AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.49 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-9-il-1000000.txt Download as CSV file: xf-ah21-9-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5055 0.09322 0.09158 -0.0228 1.0000 0.0097
-9.000 -0.5081 0.08970 0.08808 -0.0234 1.0000 0.0097
-8.750 -0.5131 0.08598 0.08438 -0.0239 1.0000 0.0098
-8.500 -0.5203 0.08240 0.08083 -0.0242 1.0000 0.0098
-8.250 -0.5311 0.07928 0.07774 -0.0238 1.0000 0.0098
-8.000 -0.5501 0.07659 0.07510 -0.0224 1.0000 0.0098
-7.750 -0.5593 0.07245 0.07097 -0.0247 1.0000 0.0098
-7.500 -0.5415 0.06345 0.06188 -0.0361 0.9977 0.0098
-7.250 -0.5224 0.05503 0.05331 -0.0445 0.9954 0.0098
-7.000 -0.5049 0.04726 0.04533 -0.0499 0.9931 0.0098
-6.750 -0.4893 0.04026 0.03803 -0.0531 0.9898 0.0098
-6.250 -0.4567 0.02238 0.01888 -0.0584 0.9847 0.0087
-6.000 -0.4296 0.01808 0.01398 -0.0590 0.9838 0.0093
-5.750 -0.3969 0.01785 0.01359 -0.0601 0.9832 0.0098
-5.500 -0.3799 0.01414 0.00943 -0.0586 0.9800 0.0106
-5.250 -0.3525 0.01343 0.00865 -0.0588 0.9780 0.0113
-5.000 -0.3228 0.01292 0.00806 -0.0594 0.9764 0.0121
-4.750 -0.2921 0.01246 0.00755 -0.0601 0.9751 0.0133
-4.500 -0.2604 0.01212 0.00715 -0.0610 0.9740 0.0144
-4.250 -0.2279 0.01186 0.00682 -0.0621 0.9731 0.0150
-4.000 -0.1986 0.01016 0.00498 -0.0626 0.9722 0.0159
-3.750 -0.1663 0.00947 0.00424 -0.0638 0.9715 0.0175
-3.500 -0.1327 0.00908 0.00382 -0.0651 0.9708 0.0188
-3.250 -0.0986 0.00873 0.00343 -0.0666 0.9702 0.0201
-3.000 -0.0768 0.00844 0.00310 -0.0652 0.9657 0.0208
-2.750 -0.0460 0.00816 0.00278 -0.0658 0.9635 0.0216
-2.500 -0.0130 0.00791 0.00249 -0.0670 0.9620 0.0230
-2.250 0.0214 0.00760 0.00217 -0.0684 0.9608 0.0302
-2.000 0.0559 0.00699 0.00193 -0.0701 0.9598 0.1333
-1.750 0.0899 0.00630 0.00176 -0.0719 0.9587 0.2889
-1.500 0.1236 0.00563 0.00161 -0.0736 0.9573 0.4565
-1.250 0.1486 0.00516 0.00153 -0.0731 0.9525 0.5792
-1.000 0.1770 0.00473 0.00143 -0.0731 0.9482 0.6857
-0.750 0.2083 0.00440 0.00133 -0.0738 0.9447 0.7641
-0.500 0.2321 0.00413 0.00133 -0.0725 0.9384 0.8477
-0.250 0.2591 0.00398 0.00126 -0.0719 0.9318 0.8842
0.000 0.2848 0.00389 0.00122 -0.0711 0.9234 0.9073
0.250 0.3122 0.00382 0.00116 -0.0707 0.9144 0.9259
0.500 0.3378 0.00378 0.00111 -0.0699 0.9023 0.9425
0.750 0.3635 0.00376 0.00108 -0.0691 0.8872 0.9571
1.000 0.3915 0.00377 0.00106 -0.0689 0.8681 0.9694
1.250 0.4237 0.00384 0.00102 -0.0696 0.8351 0.9777
1.500 0.4551 0.00401 0.00101 -0.0702 0.7890 0.9853
1.750 0.4870 0.00434 0.00106 -0.0711 0.7174 0.9909
2.000 0.5169 0.00483 0.00117 -0.0717 0.6221 0.9974
2.250 0.5379 0.00536 0.00130 -0.0705 0.5255 1.0000
2.500 0.5518 0.00594 0.00146 -0.0678 0.4228 1.0000
2.750 0.5694 0.00649 0.00164 -0.0658 0.3313 1.0000
3.000 0.5885 0.00710 0.00186 -0.0643 0.2374 1.0000
3.250 0.6100 0.00759 0.00207 -0.0632 0.1714 1.0000
3.500 0.6332 0.00798 0.00227 -0.0624 0.1272 1.0000
3.750 0.6569 0.00834 0.00248 -0.0617 0.0943 1.0000
4.000 0.6813 0.00867 0.00270 -0.0611 0.0707 1.0000
4.250 0.7059 0.00897 0.00295 -0.0605 0.0543 1.0000
4.500 0.7307 0.00928 0.00320 -0.0599 0.0422 1.0000
4.750 0.7551 0.00964 0.00352 -0.0593 0.0319 1.0000
5.000 0.7802 0.00992 0.00379 -0.0588 0.0275 1.0000
5.250 0.8034 0.01048 0.00441 -0.0578 0.0225 1.0000
5.500 0.8287 0.01074 0.00469 -0.0574 0.0215 1.0000
5.750 0.8536 0.01105 0.00503 -0.0569 0.0199 1.0000
6.000 0.8780 0.01142 0.00543 -0.0562 0.0185 1.0000
6.250 0.9010 0.01199 0.00604 -0.0554 0.0165 1.0000
6.500 0.9219 0.01286 0.00704 -0.0541 0.0151 1.0000
6.750 0.9467 0.01318 0.00740 -0.0536 0.0145 1.0000
7.000 0.9709 0.01358 0.00785 -0.0530 0.0136 1.0000
7.250 0.9955 0.01389 0.00818 -0.0525 0.0124 1.0000
7.500 1.0196 0.01428 0.00856 -0.0520 0.0113 1.0000
7.750 1.0369 0.01576 0.01022 -0.0502 0.0100 1.0000
8.000 1.0613 0.01608 0.01060 -0.0496 0.0095 1.0000
8.250 1.0850 0.01651 0.01109 -0.0490 0.0088 1.0000
8.500 1.1082 0.01698 0.01161 -0.0483 0.0081 1.0000
8.750 1.1312 0.01744 0.01211 -0.0477 0.0075 1.0000
9.000 1.1498 0.01860 0.01337 -0.0463 0.0069 1.0000
9.250 1.1650 0.02042 0.01545 -0.0443 0.0063 1.0000
9.500 1.1855 0.02123 0.01638 -0.0432 0.0061 1.0000
9.750 1.2054 0.02206 0.01733 -0.0421 0.0057 1.0000
10.000 1.2245 0.02293 0.01835 -0.0409 0.0053 1.0000
10.250 1.2441 0.02362 0.01912 -0.0398 0.0050 1.0000
10.500 1.2626 0.02440 0.01999 -0.0386 0.0048 1.0000
10.750 1.2793 0.02534 0.02103 -0.0372 0.0046 1.0000
11.000 1.2892 0.02711 0.02301 -0.0348 0.0043 1.0000
11.250 1.2920 0.02962 0.02580 -0.0316 0.0042 1.0000
11.500 1.2818 0.03310 0.02968 -0.0268 0.0041 1.0000
11.750 1.2679 0.03600 0.03286 -0.0216 0.0041 1.0000
12.000 1.2466 0.03946 0.03663 -0.0163 0.0041 1.0000
12.250 1.2182 0.04377 0.04124 -0.0119 0.0040 1.0000
12.500 1.2023 0.04723 0.04489 -0.0097 0.0041 1.0000
12.750 1.1763 0.05232 0.05019 -0.0090 0.0040 1.0000
13.000 1.1545 0.05794 0.05598 -0.0105 0.0040 1.0000
13.250 1.1440 0.06304 0.06119 -0.0133 0.0041 1.0000
13.500 1.1259 0.07153 0.06983 -0.0198 0.0041 1.0000
13.750 1.1116 0.08253 0.08096 -0.0280 0.0042 1.0000
14.000 1.0878 0.09554 0.09407 -0.0354 0.0043 1.0000
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Polar data table (+)
Polar graphs
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