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=9
| 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: 85.85 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe765-il-1000000.txt Download as CSV file: xf-goe765-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -1.1684 0.08554 0.08239 -0.0283 1.0000 0.0185
-18.750 -1.2043 0.07599 0.07267 -0.0338 1.0000 0.0184
-18.500 -1.2340 0.06720 0.06371 -0.0392 1.0000 0.0185
-18.250 -1.2463 0.06110 0.05750 -0.0432 1.0000 0.0187
-18.000 -1.2601 0.05518 0.05144 -0.0469 1.0000 0.0188
-17.750 -1.2741 0.04983 0.04594 -0.0497 1.0000 0.0188
-17.500 -1.2770 0.04633 0.04235 -0.0511 1.0000 0.0190
-17.250 -1.2831 0.04285 0.03875 -0.0519 1.0000 0.0191
-17.000 -1.2854 0.04009 0.03590 -0.0520 1.0000 0.0193
-16.750 -1.2863 0.03768 0.03338 -0.0516 1.0000 0.0195
-16.500 -1.2852 0.03564 0.03124 -0.0508 1.0000 0.0197
-16.250 -1.2817 0.03392 0.02943 -0.0497 1.0000 0.0199
-16.000 -1.2774 0.03235 0.02777 -0.0484 1.0000 0.0201
-15.750 -1.2733 0.03086 0.02618 -0.0468 1.0000 0.0203
-15.500 -1.2651 0.02971 0.02495 -0.0453 1.0000 0.0205
-15.250 -1.2575 0.02857 0.02372 -0.0435 1.0000 0.0206
-15.000 -1.2581 0.02697 0.02202 -0.0409 1.0000 0.0209
-14.750 -1.2544 0.02570 0.02070 -0.0384 1.0000 0.0213
-14.500 -1.2481 0.02461 0.01955 -0.0359 1.0000 0.0214
-14.250 -1.2366 0.02386 0.01876 -0.0340 1.0000 0.0218
-14.000 -1.2233 0.02321 0.01808 -0.0321 1.0000 0.0222
-13.750 -1.2108 0.02252 0.01734 -0.0301 1.0000 0.0225
-13.500 -1.1977 0.02186 0.01662 -0.0280 1.0000 0.0229
-13.250 -1.1837 0.02126 0.01596 -0.0261 1.0000 0.0233
-13.000 -1.1685 0.02071 0.01536 -0.0242 1.0000 0.0236
-12.750 -1.1529 0.02020 0.01478 -0.0223 1.0000 0.0239
-12.500 -1.1389 0.01958 0.01411 -0.0201 1.0000 0.0241
-12.250 -1.1287 0.01875 0.01325 -0.0174 1.0000 0.0247
-12.000 -1.1141 0.01817 0.01264 -0.0152 1.0000 0.0252
-11.750 -1.0973 0.01771 0.01216 -0.0133 1.0000 0.0257
-11.500 -1.0789 0.01735 0.01178 -0.0117 1.0000 0.0263
-11.250 -1.0615 0.01692 0.01132 -0.0098 1.0000 0.0268
-11.000 -1.0429 0.01656 0.01092 -0.0081 1.0000 0.0273
-10.750 -1.0238 0.01623 0.01055 -0.0065 1.0000 0.0278
-10.500 -0.9813 0.01532 0.00960 -0.0102 0.9556 0.0289
-10.250 -0.9401 0.01485 0.00906 -0.0133 0.9213 0.0300
-10.000 -0.9202 0.01462 0.00871 -0.0116 0.8916 0.0308
-9.750 -0.9012 0.01442 0.00839 -0.0098 0.8721 0.0316
-9.250 -0.8647 0.01370 0.00755 -0.0059 0.8424 0.0337
-9.000 -0.8440 0.01344 0.00725 -0.0044 0.8306 0.0348
-8.750 -0.8230 0.01323 0.00696 -0.0029 0.8193 0.0360
-8.500 -0.8022 0.01293 0.00661 -0.0015 0.8089 0.0373
-8.250 -0.7811 0.01265 0.00631 0.0000 0.7992 0.0391
-8.000 -0.7588 0.01244 0.00606 0.0012 0.7895 0.0406
-7.750 -0.7366 0.01222 0.00578 0.0024 0.7805 0.0424
-7.500 -0.7142 0.01193 0.00549 0.0036 0.7715 0.0446
-7.250 -0.6909 0.01176 0.00527 0.0047 0.7628 0.0467
-7.000 -0.6676 0.01150 0.00499 0.0057 0.7542 0.0491
-6.750 -0.6441 0.01129 0.00476 0.0067 0.7457 0.0519
-6.500 -0.6197 0.01110 0.00455 0.0075 0.7375 0.0547
-6.250 -0.5962 0.01087 0.00431 0.0085 0.7288 0.0584
-6.000 -0.5715 0.01070 0.00413 0.0093 0.7207 0.0620
-5.750 -0.5476 0.01048 0.00391 0.0102 0.7120 0.0669
-5.500 -0.5229 0.01031 0.00373 0.0110 0.7038 0.0715
-5.250 -0.4985 0.01012 0.00355 0.0118 0.6954 0.0773
-5.000 -0.4741 0.00994 0.00337 0.0126 0.6875 0.0842
-4.750 -0.4492 0.00977 0.00322 0.0134 0.6794 0.0919
-4.500 -0.4248 0.00962 0.00306 0.0142 0.6714 0.1004
-4.250 -0.3999 0.00942 0.00292 0.0149 0.6641 0.1118
-4.000 -0.3755 0.00925 0.00278 0.0158 0.6562 0.1241
-3.750 -0.3507 0.00909 0.00265 0.0165 0.6485 0.1374
-3.500 -0.3261 0.00892 0.00253 0.0173 0.6402 0.1533
-3.250 -0.3016 0.00877 0.00241 0.0181 0.6326 0.1712
-3.000 -0.2768 0.00860 0.00231 0.0188 0.6243 0.1910
-2.750 -0.2528 0.00844 0.00221 0.0197 0.6160 0.2142
-2.500 -0.2283 0.00826 0.00212 0.0205 0.6084 0.2420
-2.250 -0.2044 0.00810 0.00203 0.0214 0.5998 0.2697
-2.000 -0.1802 0.00792 0.00195 0.0223 0.5916 0.3014
-1.750 -0.1571 0.00773 0.00187 0.0233 0.5832 0.3393
-1.500 -0.1360 0.00743 0.00177 0.0248 0.5753 0.3981
-1.250 -0.1207 0.00693 0.00164 0.0274 0.5668 0.5047
-1.000 -0.1154 0.00627 0.00150 0.0322 0.5596 0.6465
-0.750 -0.1105 0.00576 0.00144 0.0374 0.5519 0.7635
-0.500 -0.0894 0.00559 0.00149 0.0392 0.5433 0.8346
-0.250 -0.0584 0.00559 0.00157 0.0388 0.5338 0.8667
0.000 -0.0266 0.00567 0.00164 0.0382 0.5244 0.8848
0.250 0.0020 0.00575 0.00170 0.0383 0.5147 0.8975
0.500 0.0319 0.00587 0.00179 0.0381 0.5049 0.9078
0.750 0.0653 0.00602 0.00190 0.0372 0.4943 0.9155
1.000 0.0930 0.00620 0.00205 0.0375 0.4847 0.9244
1.500 0.1682 0.00663 0.00239 0.0338 0.4623 0.9319
1.750 0.2086 0.00689 0.00258 0.0312 0.4509 0.9341
2.000 0.2436 0.00712 0.00275 0.0299 0.4398 0.9367
2.250 0.2599 0.00724 0.00284 0.0326 0.4306 0.9431
2.500 0.3019 0.00750 0.00304 0.0297 0.4190 0.9437
2.750 0.3425 0.00775 0.00324 0.0270 0.4075 0.9443
3.000 0.3822 0.00798 0.00343 0.0246 0.3970 0.9449
3.250 0.4209 0.00824 0.00362 0.0224 0.3860 0.9458
3.500 0.4561 0.00839 0.00375 0.0209 0.3762 0.9467
3.750 0.4884 0.00855 0.00386 0.0199 0.3665 0.9479
4.000 0.5192 0.00867 0.00395 0.0193 0.3578 0.9492
4.250 0.5482 0.00880 0.00405 0.0190 0.3490 0.9509
4.500 0.5581 0.00889 0.00413 0.0228 0.3420 0.9571
4.750 0.5911 0.00902 0.00422 0.0216 0.3330 0.9576
5.000 0.6238 0.00913 0.00431 0.0205 0.3245 0.9581
5.250 0.6558 0.00928 0.00442 0.0195 0.3157 0.9587
5.500 0.6879 0.00941 0.00453 0.0185 0.3062 0.9594
5.750 0.7194 0.00956 0.00466 0.0176 0.2973 0.9603
6.000 0.7501 0.00973 0.00479 0.0168 0.2875 0.9612
6.250 0.7801 0.00988 0.00492 0.0162 0.2782 0.9623
6.500 0.8086 0.01009 0.00508 0.0159 0.2674 0.9638
6.750 0.8358 0.01025 0.00523 0.0159 0.2578 0.9658
7.000 0.8474 0.01046 0.00542 0.0191 0.2500 0.9705
7.250 0.8786 0.01064 0.00556 0.0182 0.2389 0.9711
7.500 0.9099 0.01084 0.00573 0.0172 0.2277 0.9717
7.750 0.9405 0.01110 0.00594 0.0162 0.2154 0.9724
8.000 0.9705 0.01138 0.00617 0.0154 0.2038 0.9733
8.250 0.9991 0.01168 0.00641 0.0148 0.1909 0.9743
8.500 1.0268 0.01196 0.00666 0.0145 0.1795 0.9756
8.750 1.0526 0.01229 0.00695 0.0144 0.1677 0.9772
9.000 1.0754 0.01266 0.00727 0.0150 0.1561 0.9796
9.250 1.0914 0.01308 0.00765 0.0170 0.1456 0.9829
9.500 1.1199 0.01348 0.00798 0.0162 0.1325 0.9836
9.750 1.1475 0.01393 0.00837 0.0155 0.1201 0.9844
10.250 1.1996 0.01491 0.00924 0.0146 0.0979 0.9869
10.500 1.2242 0.01542 0.00971 0.0144 0.0888 0.9886
10.750 1.2462 0.01594 0.01021 0.0147 0.0809 0.9906
11.000 1.2628 0.01653 0.01077 0.0161 0.0742 0.9931
11.250 1.2857 0.01714 0.01134 0.0159 0.0672 0.9943
11.500 1.3098 0.01768 0.01188 0.0155 0.0616 0.9956
11.750 1.3300 0.01825 0.01245 0.0156 0.0566 0.9976
12.000 1.3461 0.01896 0.01314 0.0163 0.0521 0.9996
12.250 1.3477 0.01959 0.01382 0.0197 0.0500 1.0000
12.500 1.3422 0.02042 0.01469 0.0240 0.0481 1.0000
12.750 1.3371 0.02147 0.01576 0.0278 0.0459 1.0000
13.000 1.3374 0.02243 0.01677 0.0307 0.0443 1.0000
13.250 1.3375 0.02353 0.01791 0.0334 0.0426 1.0000
13.500 1.3355 0.02489 0.01930 0.0360 0.0408 1.0000
13.750 1.3355 0.02625 0.02069 0.0382 0.0392 1.0000
14.000 1.3373 0.02760 0.02209 0.0400 0.0379 1.0000
14.250 1.3369 0.02921 0.02374 0.0418 0.0365 1.0000
14.500 1.3339 0.03113 0.02570 0.0434 0.0351 1.0000
14.750 1.3350 0.03285 0.02748 0.0447 0.0340 1.0000
15.000 1.3353 0.03471 0.02940 0.0457 0.0329 1.0000
15.250 1.3338 0.03683 0.03156 0.0467 0.0318 1.0000
15.500 1.3299 0.03925 0.03403 0.0474 0.0308 1.0000
15.750 1.3252 0.04186 0.03670 0.0480 0.0300 1.0000
16.000 1.3257 0.04409 0.03900 0.0483 0.0292 1.0000
16.250 1.3227 0.04678 0.04176 0.0485 0.0284 1.0000
16.500 1.3194 0.04959 0.04463 0.0485 0.0279 1.0000
16.750 1.3124 0.05293 0.04803 0.0483 0.0271 1.0000
17.000 1.3022 0.05675 0.05191 0.0478 0.0264 1.0000
17.250 1.2963 0.06016 0.05541 0.0473 0.0258 1.0000
17.500 1.2918 0.06349 0.05881 0.0467 0.0254 1.0000
17.750 1.2860 0.06701 0.06242 0.0460 0.0248 1.0000
18.000 1.2785 0.07085 0.06634 0.0451 0.0245 1.0000
18.250 1.2693 0.07499 0.07055 0.0440 0.0240 1.0000
18.500 1.2586 0.07942 0.07505 0.0427 0.0237 1.0000
18.750 1.2465 0.08409 0.07980 0.0413 0.0231 1.0000
19.000 1.2318 0.08925 0.08502 0.0396 0.0227 1.0000
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Polar data table (+)
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