AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 50,000 Max Cl/Cd: 35.56 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-7-il-50000.txt Download as CSV file: xf-ah21-7-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 7% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4481 0.09690 0.09003 -0.0134 1.0000 0.3076
-7.500 -0.4527 0.09445 0.08767 -0.0116 1.0000 0.3202
-7.250 -0.4603 0.09233 0.08565 -0.0095 1.0000 0.3335
-7.000 -0.4633 0.08985 0.08325 -0.0071 1.0000 0.3484
-6.750 -0.4606 0.08708 0.08053 -0.0046 1.0000 0.3646
-6.500 -0.4586 0.08460 0.07811 -0.0017 1.0000 0.3854
-6.250 -0.4769 0.08338 0.07704 0.0025 1.0000 0.4040
-5.250 -0.5002 0.05094 0.04327 -0.0356 1.0000 0.1498
-5.000 -0.4803 0.04569 0.03734 -0.0370 1.0000 0.1357
-4.750 -0.4604 0.04208 0.03336 -0.0370 1.0000 0.1334
-4.500 -0.4381 0.03868 0.02946 -0.0370 1.0000 0.1312
-4.250 -0.4134 0.03553 0.02569 -0.0369 1.0000 0.1284
-4.000 -0.3878 0.03291 0.02254 -0.0364 1.0000 0.1279
-3.750 -0.3622 0.03082 0.02007 -0.0358 1.0000 0.1303
-3.500 -0.3361 0.02923 0.01794 -0.0351 1.0000 0.1377
-3.250 -0.3115 0.02754 0.01626 -0.0343 1.0000 0.1473
-3.000 -0.2862 0.02601 0.01464 -0.0331 1.0000 0.1595
-2.750 -0.2618 0.02466 0.01336 -0.0320 1.0000 0.1873
-2.500 -0.2367 0.02291 0.01201 -0.0311 1.0000 0.2588
-2.250 -0.1987 0.01939 0.01175 -0.0261 1.0000 1.0000
-2.000 -0.1826 0.01922 0.01104 -0.0250 1.0000 1.0000
-1.750 -0.1636 0.01918 0.01055 -0.0242 1.0000 1.0000
-1.500 -0.1433 0.01921 0.01020 -0.0235 1.0000 1.0000
-1.250 -0.1225 0.01929 0.00994 -0.0228 1.0000 1.0000
-1.000 -0.1014 0.01942 0.00978 -0.0222 1.0000 1.0000
-0.750 -0.0802 0.01959 0.00969 -0.0216 1.0000 1.0000
-0.500 -0.0589 0.01979 0.00965 -0.0211 1.0000 1.0000
-0.250 -0.0376 0.02002 0.00969 -0.0205 1.0000 1.0000
0.000 -0.0164 0.02028 0.00978 -0.0200 1.0000 1.0000
0.250 0.0047 0.02058 0.00993 -0.0195 1.0000 1.0000
0.500 0.0256 0.02091 0.01012 -0.0190 1.0000 1.0000
0.750 0.0463 0.02127 0.01038 -0.0185 1.0000 1.0000
1.000 0.0668 0.02167 0.01068 -0.0180 1.0000 1.0000
1.250 0.0871 0.02210 0.01105 -0.0175 1.0000 1.0000
1.500 0.1070 0.02257 0.01147 -0.0171 1.0000 1.0000
1.750 0.1267 0.02309 0.01195 -0.0166 1.0000 1.0000
2.000 0.1459 0.02365 0.01249 -0.0162 1.0000 1.0000
2.250 0.1648 0.02426 0.01309 -0.0159 1.0000 1.0000
2.500 0.1833 0.02493 0.01377 -0.0155 1.0000 1.0000
2.750 0.2012 0.02565 0.01452 -0.0152 1.0000 1.0000
3.000 0.2187 0.02644 0.01535 -0.0149 1.0000 1.0000
3.250 0.2355 0.02731 0.01627 -0.0148 1.0000 1.0000
3.500 0.2517 0.02827 0.01731 -0.0146 1.0000 1.0000
3.750 0.2894 0.02986 0.01903 -0.0188 0.9885 1.0000
4.000 0.3626 0.03194 0.02135 -0.0288 0.9578 1.0000
4.250 0.4214 0.03292 0.02260 -0.0354 0.9245 1.0000
4.500 0.4901 0.03333 0.02334 -0.0424 0.8897 1.0000
4.750 0.5540 0.03277 0.02318 -0.0472 0.8512 1.0000
5.000 0.6265 0.03090 0.02179 -0.0512 0.8095 1.0000
5.250 0.7110 0.02675 0.01831 -0.0537 0.7606 1.0000
5.500 0.7867 0.02227 0.01420 -0.0529 0.6540 1.0000
5.750 0.8187 0.02302 0.01337 -0.0488 0.4273 1.0000
6.000 0.8365 0.02549 0.01480 -0.0464 0.3192 1.0000
6.250 0.8681 0.02785 0.01662 -0.0468 0.2561 1.0000
6.500 0.9010 0.03009 0.01874 -0.0473 0.2188 1.0000
6.750 0.9303 0.03227 0.02089 -0.0473 0.1938 1.0000
7.000 0.9598 0.03475 0.02352 -0.0472 0.1778 1.0000
7.250 0.9836 0.03713 0.02609 -0.0464 0.1643 1.0000
7.500 1.0088 0.03999 0.02906 -0.0459 0.1551 1.0000
7.750 1.0250 0.04285 0.03255 -0.0437 0.1492 1.0000
8.000 1.0455 0.04587 0.03560 -0.0428 0.1415 1.0000
8.250 1.0528 0.04912 0.03953 -0.0397 0.1386 1.0000
8.500 1.0589 0.05292 0.04387 -0.0368 0.1375 1.0000
8.750 1.0602 0.05691 0.04835 -0.0338 0.1370 1.0000
9.000 1.0572 0.06094 0.05282 -0.0307 0.1362 1.0000
9.250 1.0496 0.06521 0.05746 -0.0277 0.1362 1.0000
9.500 1.0373 0.06966 0.06223 -0.0248 0.1368 1.0000
9.750 1.0222 0.07433 0.06714 -0.0223 0.1383 1.0000
10.000 1.0091 0.07910 0.07206 -0.0203 0.1402 1.0000
10.250 0.9942 0.08401 0.07711 -0.0187 0.1436 1.0000
10.500 0.9150 0.09324 0.08647 -0.0210 0.1595 1.0000
10.750 0.8998 0.10188 0.09511 -0.0244 0.1703 1.0000
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Polar data table (+)
Polar graphs
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