Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=500,000 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: 500,000 Max Cl/Cd: 68.47 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe765-il-500000-n5.txt Download as CSV file: xf-goe765-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.9369 0.12533 0.12213 -0.0054 1.0000 0.0190
-18.750 -0.9761 0.11360 0.11024 -0.0124 1.0000 0.0191
-18.500 -1.0143 0.10275 0.09922 -0.0188 1.0000 0.0191
-18.250 -1.0507 0.09261 0.08892 -0.0247 1.0000 0.0190
-18.000 -1.0839 0.08309 0.07924 -0.0304 1.0000 0.0191
-17.750 -1.1160 0.07371 0.06968 -0.0361 1.0000 0.0190
-17.500 -1.1392 0.06569 0.06148 -0.0413 1.0000 0.0192
-17.250 -1.1595 0.05854 0.05415 -0.0458 1.0000 0.0192
-17.000 -1.1724 0.05317 0.04863 -0.0488 1.0000 0.0193
-16.750 -1.1823 0.04879 0.04409 -0.0506 1.0000 0.0195
-16.500 -1.1900 0.04516 0.04032 -0.0515 1.0000 0.0196
-16.250 -1.1941 0.04225 0.03729 -0.0516 1.0000 0.0199
-16.000 -1.1971 0.03970 0.03461 -0.0511 1.0000 0.0200
-15.750 -1.1985 0.03748 0.03227 -0.0502 1.0000 0.0202
-15.500 -1.1973 0.03561 0.03026 -0.0489 1.0000 0.0204
-15.250 -1.1954 0.03389 0.02843 -0.0474 1.0000 0.0206
-15.000 -1.1937 0.03228 0.02674 -0.0456 1.0000 0.0208
-14.750 -1.1907 0.03083 0.02521 -0.0436 1.0000 0.0210
-14.500 -1.1857 0.02956 0.02388 -0.0416 1.0000 0.0213
-14.250 -1.1772 0.02854 0.02281 -0.0397 1.0000 0.0216
-14.000 -1.1687 0.02755 0.02174 -0.0377 1.0000 0.0220
-13.750 -1.1590 0.02664 0.02076 -0.0356 1.0000 0.0223
-13.500 -1.1487 0.02577 0.01982 -0.0335 1.0000 0.0227
-13.250 -1.1373 0.02497 0.01895 -0.0315 1.0000 0.0231
-13.000 -1.1247 0.02424 0.01813 -0.0295 1.0000 0.0235
-12.750 -1.1121 0.02351 0.01733 -0.0274 1.0000 0.0238
-12.500 -1.0994 0.02279 0.01654 -0.0253 1.0000 0.0242
-12.250 -1.0869 0.02206 0.01578 -0.0231 1.0000 0.0246
-12.000 -1.0727 0.02143 0.01511 -0.0211 1.0000 0.0251
-11.750 -1.0572 0.02086 0.01450 -0.0192 1.0000 0.0256
-11.500 -1.0407 0.02034 0.01394 -0.0174 1.0000 0.0262
-11.250 -1.0242 0.01982 0.01337 -0.0155 1.0000 0.0268
-11.000 -1.0068 0.01935 0.01284 -0.0138 1.0000 0.0274
-10.750 -0.9709 0.01862 0.01207 -0.0161 0.9465 0.0283
-10.500 -0.9334 0.01799 0.01135 -0.0185 0.9134 0.0292
-10.250 -0.9122 0.01761 0.01086 -0.0174 0.8866 0.0300
-10.000 -0.8939 0.01727 0.01040 -0.0155 0.8668 0.0309
-9.750 -0.8752 0.01695 0.00997 -0.0138 0.8514 0.0317
-9.500 -0.8571 0.01656 0.00952 -0.0119 0.8375 0.0328
-9.250 -0.8377 0.01622 0.00913 -0.0103 0.8252 0.0339
-9.000 -0.8177 0.01591 0.00874 -0.0087 0.8142 0.0351
-8.750 -0.7974 0.01562 0.00836 -0.0072 0.8034 0.0363
-8.500 -0.7769 0.01527 0.00798 -0.0057 0.7934 0.0375
-8.000 -0.7344 0.01471 0.00731 -0.0030 0.7744 0.0406
-7.750 -0.7128 0.01445 0.00698 -0.0017 0.7657 0.0423
-7.500 -0.6907 0.01416 0.00669 -0.0005 0.7567 0.0444
-7.250 -0.6682 0.01393 0.00640 0.0006 0.7481 0.0467
-7.000 -0.6454 0.01366 0.00611 0.0017 0.7399 0.0490
-6.750 -0.6224 0.01342 0.00584 0.0027 0.7311 0.0517
-6.500 -0.5988 0.01320 0.00557 0.0037 0.7232 0.0544
-6.250 -0.5753 0.01296 0.00532 0.0046 0.7145 0.0579
-6.000 -0.5514 0.01276 0.00508 0.0055 0.7067 0.0616
-5.750 -0.5276 0.01252 0.00485 0.0064 0.6978 0.0660
-5.500 -0.5036 0.01234 0.00462 0.0073 0.6900 0.0707
-5.250 -0.4793 0.01212 0.00442 0.0081 0.6812 0.0762
-5.000 -0.4553 0.01194 0.00421 0.0090 0.6725 0.0821
-4.750 -0.4308 0.01175 0.00403 0.0098 0.6638 0.0889
-4.500 -0.4067 0.01156 0.00384 0.0106 0.6551 0.0969
-4.250 -0.3821 0.01138 0.00367 0.0114 0.6470 0.1052
-4.000 -0.3576 0.01122 0.00351 0.0122 0.6383 0.1153
-3.750 -0.3331 0.01105 0.00336 0.0130 0.6305 0.1271
-3.500 -0.3087 0.01087 0.00321 0.0138 0.6221 0.1408
-3.250 -0.2843 0.01071 0.00308 0.0146 0.6145 0.1553
-3.000 -0.2598 0.01054 0.00296 0.0154 0.6062 0.1724
-2.750 -0.2357 0.01039 0.00284 0.0162 0.5978 0.1915
-2.500 -0.2114 0.01021 0.00273 0.0170 0.5893 0.2132
-2.000 -0.1633 0.00988 0.00254 0.0187 0.5723 0.2641
-1.750 -0.1399 0.00972 0.00245 0.0197 0.5635 0.2950
-1.500 -0.1167 0.00952 0.00237 0.0207 0.5550 0.3292
-1.250 -0.0950 0.00929 0.00227 0.0220 0.5461 0.3757
-1.000 -0.0764 0.00891 0.00217 0.0239 0.5377 0.4485
-0.750 -0.0667 0.00833 0.00203 0.0277 0.5296 0.5687
-0.500 -0.0602 0.00777 0.00194 0.0323 0.5220 0.6901
-0.250 -0.0368 0.00742 0.00203 0.0337 0.5125 0.8019
0.000 0.0106 0.00749 0.00220 0.0298 0.5017 0.8497
0.250 0.0564 0.00768 0.00237 0.0263 0.4903 0.8744
0.500 0.0951 0.00787 0.00253 0.0242 0.4794 0.8874
0.750 0.1225 0.00803 0.00264 0.0246 0.4700 0.8978
1.000 0.1570 0.00826 0.00281 0.0234 0.4585 0.9045
1.750 0.2513 0.00890 0.00330 0.0218 0.4276 0.9195
2.000 0.2673 0.00902 0.00338 0.0245 0.4193 0.9276
2.250 0.3066 0.00929 0.00359 0.0223 0.4084 0.9290
2.500 0.3443 0.00954 0.00380 0.0203 0.3983 0.9307
2.750 0.3773 0.00973 0.00393 0.0193 0.3883 0.9323
3.000 0.4074 0.00986 0.00403 0.0188 0.3789 0.9341
3.500 0.4473 0.01005 0.00415 0.0221 0.3627 0.9425
3.750 0.4793 0.01020 0.00427 0.0212 0.3538 0.9432
4.000 0.5110 0.01033 0.00438 0.0203 0.3455 0.9440
4.250 0.5415 0.01050 0.00450 0.0197 0.3364 0.9449
4.500 0.5723 0.01064 0.00462 0.0190 0.3282 0.9460
4.750 0.6019 0.01081 0.00476 0.0185 0.3195 0.9473
5.000 0.6307 0.01095 0.00490 0.0182 0.3111 0.9489
5.250 0.6570 0.01113 0.00504 0.0183 0.3022 0.9509
5.500 0.6793 0.01127 0.00518 0.0194 0.2947 0.9541
5.750 0.6994 0.01144 0.00533 0.0209 0.2864 0.9573
6.000 0.7296 0.01162 0.00549 0.0202 0.2768 0.9580
6.250 0.7591 0.01184 0.00568 0.0196 0.2666 0.9589
6.500 0.7887 0.01205 0.00587 0.0190 0.2563 0.9600
6.750 0.8173 0.01229 0.00609 0.0186 0.2462 0.9613
7.000 0.8440 0.01256 0.00632 0.0185 0.2353 0.9629
7.250 0.8691 0.01281 0.00655 0.0187 0.2240 0.9648
7.500 0.8908 0.01309 0.00681 0.0197 0.2140 0.9675
7.750 0.9092 0.01340 0.00709 0.0213 0.2036 0.9706
8.000 0.9374 0.01374 0.00739 0.0207 0.1911 0.9715
8.250 0.9647 0.01409 0.00771 0.0203 0.1793 0.9725
8.500 0.9907 0.01448 0.00807 0.0201 0.1671 0.9738
8.750 1.0155 0.01491 0.00845 0.0201 0.1553 0.9755
9.000 1.0386 0.01539 0.00889 0.0203 0.1431 0.9776
9.250 1.0576 0.01588 0.00934 0.0214 0.1328 0.9804
9.500 1.0749 0.01635 0.00980 0.0229 0.1233 0.9828
9.750 1.0998 0.01688 0.01030 0.0225 0.1129 0.9840
10.000 1.1236 0.01747 0.01085 0.0223 0.1029 0.9855
10.250 1.1455 0.01808 0.01145 0.0224 0.0944 0.9874
10.500 1.1637 0.01872 0.01207 0.0231 0.0864 0.9897
10.750 1.1772 0.01930 0.01266 0.0248 0.0807 0.9924
11.000 1.1917 0.02001 0.01338 0.0258 0.0744 0.9945
11.250 1.2086 0.02085 0.01422 0.0259 0.0681 0.9967
11.500 1.2252 0.02171 0.01510 0.0260 0.0637 0.9986
11.750 1.2384 0.02282 0.01622 0.0263 0.0590 1.0000
12.000 1.2377 0.02378 0.01723 0.0294 0.0564 1.0000
12.250 1.2363 0.02493 0.01841 0.0324 0.0537 1.0000
12.500 1.2352 0.02620 0.01971 0.0350 0.0513 1.0000
12.750 1.2357 0.02749 0.02104 0.0372 0.0488 1.0000
13.000 1.2357 0.02894 0.02253 0.0392 0.0469 1.0000
13.250 1.2355 0.03052 0.02415 0.0410 0.0451 1.0000
13.500 1.2365 0.03211 0.02580 0.0425 0.0434 1.0000
13.750 1.2362 0.03391 0.02764 0.0439 0.0416 1.0000
14.000 1.2349 0.03590 0.02968 0.0451 0.0402 1.0000
14.250 1.2346 0.03789 0.03173 0.0461 0.0389 1.0000
14.500 1.2341 0.04000 0.03391 0.0468 0.0375 1.0000
14.750 1.2317 0.04236 0.03632 0.0475 0.0359 1.0000
15.000 1.2284 0.04493 0.03894 0.0479 0.0351 1.0000
15.250 1.2260 0.04752 0.04161 0.0482 0.0341 1.0000
15.500 1.2241 0.05015 0.04432 0.0483 0.0330 1.0000
15.750 1.2205 0.05309 0.04732 0.0482 0.0320 1.0000
16.000 1.2161 0.05621 0.05051 0.0479 0.0312 1.0000
16.250 1.2093 0.05971 0.05407 0.0474 0.0303 1.0000
16.500 1.2052 0.06298 0.05742 0.0469 0.0298 1.0000
16.750 1.2007 0.06637 0.06090 0.0463 0.0290 1.0000
17.000 1.1951 0.06997 0.06458 0.0455 0.0283 1.0000
17.250 1.1884 0.07379 0.06848 0.0445 0.0277 1.0000
17.500 1.1808 0.07781 0.07257 0.0434 0.0271 1.0000
17.750 1.1723 0.08201 0.07685 0.0422 0.0265 1.0000
18.000 1.1633 0.08637 0.08128 0.0409 0.0262 1.0000
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Polar data table (+)
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