Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.57 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe765-il-1000000-n5.txt Download as CSV file: xf-goe765-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Gottingen 765 airfoil (recovered). Thick: .144 L
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -1.1571 0.09636 0.09320 -0.0217 1.0000 0.0148
-19.250 -1.2382 0.07944 0.07601 -0.0314 1.0000 0.0147
-19.000 -1.2965 0.06556 0.06187 -0.0401 1.0000 0.0146
-18.750 -1.3289 0.05626 0.05236 -0.0463 1.0000 0.0146
-18.500 -1.3475 0.05011 0.04603 -0.0497 1.0000 0.0146
-18.250 -1.3502 0.04665 0.04246 -0.0511 1.0000 0.0148
-18.000 -1.3599 0.04275 0.03843 -0.0521 1.0000 0.0149
-17.750 -1.3669 0.03956 0.03512 -0.0522 1.0000 0.0149
-17.500 -1.3704 0.03696 0.03243 -0.0517 1.0000 0.0151
-17.250 -1.3714 0.03480 0.03018 -0.0507 1.0000 0.0153
-17.000 -1.3699 0.03297 0.02827 -0.0495 1.0000 0.0154
-16.750 -1.3666 0.03138 0.02660 -0.0480 1.0000 0.0156
-16.500 -1.3614 0.03001 0.02516 -0.0464 1.0000 0.0158
-16.250 -1.3548 0.02879 0.02388 -0.0447 1.0000 0.0160
-16.000 -1.3474 0.02767 0.02269 -0.0429 1.0000 0.0162
-15.750 -1.3392 0.02664 0.02159 -0.0410 1.0000 0.0164
-15.500 -1.3291 0.02574 0.02063 -0.0392 1.0000 0.0166
-15.250 -1.3191 0.02487 0.01969 -0.0372 1.0000 0.0168
-15.000 -1.3075 0.02410 0.01886 -0.0353 1.0000 0.0170
-14.750 -1.2950 0.02340 0.01810 -0.0334 1.0000 0.0173
-14.500 -1.2838 0.02263 0.01726 -0.0313 1.0000 0.0173
-14.250 -1.2696 0.02204 0.01661 -0.0295 1.0000 0.0176
-14.000 -1.2578 0.02129 0.01583 -0.0273 1.0000 0.0180
-13.750 -1.2443 0.02065 0.01515 -0.0252 1.0000 0.0182
-13.500 -1.2298 0.02006 0.01452 -0.0233 1.0000 0.0185
-13.250 -1.2145 0.01953 0.01395 -0.0214 1.0000 0.0189
-13.000 -1.1983 0.01903 0.01342 -0.0196 1.0000 0.0192
-12.750 -1.1816 0.01857 0.01292 -0.0178 1.0000 0.0195
-12.500 -1.1649 0.01810 0.01241 -0.0159 1.0000 0.0198
-12.250 -1.1471 0.01769 0.01197 -0.0142 1.0000 0.0202
-12.000 -1.1038 0.01709 0.01130 -0.0179 0.9477 0.0207
-11.750 -1.0689 0.01656 0.01064 -0.0199 0.9027 0.0213
-11.250 -1.0350 0.01595 0.00982 -0.0158 0.8548 0.0222
-11.000 -1.0169 0.01565 0.00944 -0.0139 0.8390 0.0228
-10.750 -0.9978 0.01535 0.00907 -0.0122 0.8259 0.0234
-10.500 -0.9783 0.01507 0.00871 -0.0106 0.8140 0.0238
-10.250 -0.9589 0.01476 0.00834 -0.0090 0.8027 0.0245
-10.000 -0.9388 0.01444 0.00798 -0.0074 0.7926 0.0252
-9.750 -0.9185 0.01416 0.00765 -0.0059 0.7826 0.0260
-9.500 -0.8974 0.01388 0.00733 -0.0046 0.7733 0.0268
-9.250 -0.8762 0.01364 0.00703 -0.0032 0.7640 0.0275
-9.000 -0.8545 0.01337 0.00673 -0.0019 0.7551 0.0283
-8.750 -0.8331 0.01312 0.00644 -0.0005 0.7461 0.0294
-8.500 -0.8108 0.01288 0.00618 0.0006 0.7382 0.0306
-8.250 -0.7886 0.01269 0.00593 0.0019 0.7294 0.0317
-8.000 -0.7660 0.01245 0.00567 0.0030 0.7219 0.0330
-7.750 -0.7432 0.01223 0.00543 0.0041 0.7132 0.0345
-7.500 -0.7198 0.01204 0.00520 0.0051 0.7058 0.0360
-7.250 -0.6961 0.01183 0.00497 0.0060 0.6973 0.0376
-7.000 -0.6723 0.01163 0.00474 0.0070 0.6894 0.0394
-6.750 -0.6479 0.01145 0.00454 0.0078 0.6814 0.0413
-6.500 -0.6239 0.01126 0.00433 0.0086 0.6731 0.0437
-6.250 -0.5993 0.01108 0.00414 0.0094 0.6651 0.0460
-6.000 -0.5749 0.01091 0.00395 0.0102 0.6561 0.0488
-5.750 -0.5503 0.01074 0.00377 0.0110 0.6479 0.0520
-5.500 -0.5255 0.01059 0.00360 0.0118 0.6384 0.0550
-5.250 -0.5007 0.01043 0.00343 0.0125 0.6305 0.0589
-5.000 -0.4758 0.01028 0.00327 0.0132 0.6218 0.0632
-4.750 -0.4509 0.01014 0.00313 0.0140 0.6140 0.0684
-4.500 -0.4259 0.00998 0.00298 0.0147 0.6056 0.0737
-4.250 -0.4008 0.00986 0.00285 0.0154 0.5982 0.0802
-4.000 -0.3756 0.00970 0.00272 0.0160 0.5909 0.0874
-3.750 -0.3506 0.00958 0.00260 0.0167 0.5821 0.0945
-3.500 -0.3252 0.00946 0.00249 0.0174 0.5742 0.1032
-3.250 -0.3001 0.00933 0.00238 0.0180 0.5659 0.1132
-3.000 -0.2750 0.00920 0.00228 0.0187 0.5575 0.1247
-2.750 -0.2500 0.00908 0.00218 0.0194 0.5484 0.1373
-2.500 -0.2250 0.00896 0.00210 0.0201 0.5408 0.1528
-2.250 -0.1998 0.00885 0.00202 0.0208 0.5317 0.1674
-2.000 -0.1749 0.00874 0.00195 0.0215 0.5227 0.1847
-1.750 -0.1499 0.00863 0.00188 0.0222 0.5140 0.2044
-1.250 -0.1006 0.00840 0.00177 0.0237 0.4955 0.2522
-1.000 -0.0759 0.00830 0.00172 0.0244 0.4869 0.2769
-0.750 -0.0518 0.00817 0.00168 0.0252 0.4774 0.3086
-0.500 -0.0281 0.00803 0.00163 0.0262 0.4683 0.3449
-0.250 -0.0055 0.00786 0.00159 0.0273 0.4586 0.3926
0.000 0.0134 0.00751 0.00152 0.0291 0.4504 0.4760
0.250 0.0248 0.00699 0.00143 0.0326 0.4418 0.6021
0.500 0.0336 0.00656 0.00136 0.0368 0.4339 0.7088
0.750 0.0441 0.00621 0.00138 0.0408 0.4256 0.8086
1.000 0.0708 0.00616 0.00148 0.0413 0.4167 0.8601
1.250 0.1031 0.00624 0.00158 0.0405 0.4058 0.8825
1.500 0.1322 0.00632 0.00166 0.0404 0.3975 0.8961
1.750 0.1654 0.00647 0.00177 0.0394 0.3869 0.9065
2.000 0.1943 0.00656 0.00184 0.0393 0.3788 0.9137
2.500 0.2460 0.00680 0.00202 0.0404 0.3624 0.9268
2.750 0.2837 0.00699 0.00216 0.0383 0.3525 0.9297
3.000 0.3182 0.00714 0.00229 0.0369 0.3444 0.9327
3.250 0.3489 0.00732 0.00243 0.0364 0.3361 0.9366
3.500 0.3646 0.00741 0.00251 0.0392 0.3302 0.9426
3.750 0.3991 0.00758 0.00263 0.0377 0.3212 0.9437
4.000 0.4320 0.00772 0.00274 0.0366 0.3140 0.9445
4.250 0.4642 0.00785 0.00285 0.0356 0.3056 0.9453
4.500 0.4956 0.00800 0.00296 0.0347 0.2981 0.9460
4.750 0.5265 0.00815 0.00308 0.0340 0.2889 0.9469
5.000 0.5565 0.00831 0.00321 0.0335 0.2810 0.9480
5.250 0.5852 0.00847 0.00334 0.0332 0.2722 0.9493
5.500 0.6122 0.00863 0.00347 0.0333 0.2640 0.9510
5.750 0.6210 0.00875 0.00357 0.0374 0.2559 0.9569
6.000 0.6524 0.00894 0.00372 0.0364 0.2468 0.9574
6.250 0.6828 0.00917 0.00390 0.0357 0.2360 0.9579
6.500 0.7132 0.00937 0.00407 0.0349 0.2260 0.9584
6.750 0.7430 0.00962 0.00428 0.0343 0.2150 0.9591
7.000 0.7720 0.00990 0.00450 0.0337 0.2032 0.9598
7.250 0.8003 0.01018 0.00474 0.0333 0.1912 0.9606
7.500 0.8281 0.01044 0.00496 0.0330 0.1811 0.9616
7.750 0.8546 0.01074 0.00522 0.0329 0.1700 0.9628
8.000 0.8796 0.01108 0.00550 0.0331 0.1576 0.9644
8.250 0.9006 0.01142 0.00579 0.0342 0.1469 0.9671
8.500 0.9150 0.01167 0.00602 0.0367 0.1387 0.9706
8.750 0.9422 0.01208 0.00637 0.0362 0.1263 0.9712
9.000 0.9696 0.01247 0.00673 0.0357 0.1167 0.9719
9.250 0.9960 0.01292 0.00712 0.0354 0.1062 0.9728
9.500 1.0210 0.01339 0.00754 0.0353 0.0964 0.9739
9.750 1.0453 0.01383 0.00795 0.0353 0.0884 0.9752
10.000 1.0676 0.01430 0.00839 0.0357 0.0810 0.9769
10.250 1.0858 0.01481 0.00887 0.0368 0.0741 0.9795
10.750 1.1204 0.01579 0.00983 0.0393 0.0625 0.9839
11.000 1.1407 0.01637 0.01039 0.0395 0.0569 0.9851
11.250 1.1598 0.01699 0.01101 0.0399 0.0524 0.9867
11.500 1.1793 0.01761 0.01164 0.0401 0.0491 0.9885
12.000 1.2100 0.01915 0.01321 0.0414 0.0429 0.9926
12.250 1.2250 0.02009 0.01415 0.0418 0.0400 0.9939
12.500 1.2445 0.02096 0.01506 0.0412 0.0379 0.9950
12.750 1.2620 0.02202 0.01613 0.0407 0.0355 0.9963
13.000 1.2786 0.02311 0.01726 0.0403 0.0338 0.9975
13.250 1.2943 0.02427 0.01845 0.0400 0.0321 0.9985
13.500 1.3081 0.02564 0.01985 0.0395 0.0305 0.9993
13.750 1.3223 0.02701 0.02126 0.0390 0.0291 0.9999
14.000 1.3254 0.02842 0.02271 0.0405 0.0282 1.0000
14.250 1.3262 0.02998 0.02432 0.0421 0.0273 1.0000
14.500 1.3262 0.03171 0.02609 0.0436 0.0263 1.0000
14.750 1.3274 0.03343 0.02786 0.0447 0.0256 1.0000
15.000 1.3283 0.03526 0.02975 0.0458 0.0249 1.0000
15.250 1.3281 0.03728 0.03182 0.0466 0.0241 1.0000
15.500 1.3262 0.03953 0.03412 0.0474 0.0232 1.0000
15.750 1.3244 0.04187 0.03651 0.0479 0.0227 1.0000
16.000 1.3229 0.04430 0.03901 0.0482 0.0221 1.0000
16.250 1.3213 0.04684 0.04162 0.0484 0.0217 1.0000
16.500 1.3195 0.04949 0.04433 0.0484 0.0212 1.0000
16.750 1.3159 0.05242 0.04734 0.0483 0.0207 1.0000
17.000 1.3112 0.05556 0.05054 0.0480 0.0202 1.0000
17.250 1.3054 0.05892 0.05397 0.0475 0.0197 1.0000
17.500 1.2984 0.06252 0.05764 0.0469 0.0193 1.0000
17.750 1.2936 0.06592 0.06111 0.0462 0.0190 1.0000
18.000 1.2874 0.06956 0.06483 0.0454 0.0188 1.0000
18.250 1.2803 0.07339 0.06875 0.0444 0.0184 1.0000
18.500 1.2726 0.07739 0.07282 0.0433 0.0181 1.0000
18.750 1.2639 0.08155 0.07706 0.0421 0.0178 1.0000
19.000 1.2546 0.08586 0.08145 0.0408 0.0175 1.0000
19.250 1.2452 0.09027 0.08594 0.0393 0.0172 1.0000
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Polar data table (+)
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