AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 82-150 F (ah82150f-il) Reynolds number: 100,000 Max Cl/Cd: 34.55 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150f-il-100000.txt Download as CSV file: xf-ah82150f-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 F
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4696 0.10690 0.10351 -0.0251 1.0000 0.1098
-7.500 -0.4945 0.10265 0.09932 -0.0261 1.0000 0.1107
-7.250 -0.5219 0.09833 0.09503 -0.0267 1.0000 0.1109
-7.000 -0.5450 0.09472 0.09144 -0.0251 1.0000 0.1105
-6.750 -0.6803 0.09233 0.08837 -0.0238 1.0000 0.0992
-6.500 -0.6629 0.08900 0.08527 -0.0209 1.0000 0.1022
-6.250 -0.6651 0.08597 0.08219 -0.0192 1.0000 0.1053
-6.000 -0.6914 0.08379 0.07926 -0.0193 1.0000 0.1127
-5.750 -0.6254 0.07589 0.07241 -0.0165 1.0000 0.1226
-5.500 -0.6834 0.07639 0.07170 -0.0168 1.0000 0.1271
-5.250 -0.6714 0.07198 0.06773 -0.0146 1.0000 0.1319
-4.750 -0.6621 0.06586 0.06118 -0.0127 1.0000 0.1574
-4.500 -0.6536 0.06320 0.05834 -0.0116 1.0000 0.1715
-4.250 -0.6438 0.06045 0.05556 -0.0101 1.0000 0.1867
-4.000 -0.6331 0.05797 0.05306 -0.0086 1.0000 0.2030
-3.750 -0.5773 0.04466 0.03686 -0.0078 1.0000 0.0699
-3.500 -0.5575 0.04255 0.03428 -0.0066 1.0000 0.0703
-3.250 -0.5384 0.03947 0.03095 -0.0060 1.0000 0.0730
-3.000 -0.5170 0.03769 0.02883 -0.0049 1.0000 0.0736
-2.750 -0.4882 0.03648 0.02738 -0.0053 0.9979 0.0763
-2.500 -0.4545 0.03646 0.02693 -0.0064 0.9945 0.0838
-2.250 -0.4270 0.03519 0.02561 -0.0068 0.9914 0.0884
-2.000 -0.3943 0.03533 0.02552 -0.0081 0.9863 0.0982
-1.750 -0.3624 0.03527 0.02559 -0.0093 0.9835 0.1076
-1.500 -0.3383 0.03473 0.02512 -0.0093 0.9771 0.1186
-1.250 -0.3066 0.03504 0.02549 -0.0106 0.9720 0.1400
-1.000 -0.2815 0.03499 0.02572 -0.0108 0.9679 0.1797
-0.750 -0.1473 0.03820 0.03166 -0.0253 0.9865 1.0000
-0.500 -0.1150 0.03901 0.03222 -0.0277 0.9762 1.0000
-0.250 -0.0845 0.03999 0.03297 -0.0298 0.9669 1.0000
0.500 -0.0013 0.04212 0.03460 -0.0338 0.9321 1.0000
0.750 0.0216 0.04273 0.03509 -0.0341 0.9200 1.0000
1.000 0.0447 0.04340 0.03566 -0.0344 0.9082 1.0000
1.250 0.0695 0.04414 0.03630 -0.0349 0.8961 1.0000
1.500 0.0966 0.04497 0.03702 -0.0358 0.8844 1.0000
1.750 0.1255 0.04529 0.03725 -0.0365 0.8650 1.0000
2.000 0.2146 0.04474 0.03650 -0.0448 0.8208 1.0000
2.250 0.2406 0.04488 0.03658 -0.0447 0.8074 1.0000
2.500 0.2616 0.04505 0.03670 -0.0439 0.7953 1.0000
2.750 0.2848 0.04528 0.03689 -0.0434 0.7848 1.0000
3.000 0.3194 0.04551 0.03709 -0.0447 0.7773 1.0000
3.250 0.3289 0.04564 0.03721 -0.0421 0.7656 1.0000
3.500 0.3445 0.04581 0.03737 -0.0405 0.7552 1.0000
3.750 0.3811 0.04593 0.03749 -0.0419 0.7494 1.0000
4.000 0.3878 0.04607 0.03764 -0.0390 0.7380 1.0000
4.250 0.4004 0.04624 0.03781 -0.0369 0.7281 1.0000
4.500 0.4340 0.04622 0.03781 -0.0378 0.7225 1.0000
4.750 0.4410 0.04637 0.03798 -0.0349 0.7114 1.0000
5.000 0.4817 0.04618 0.03785 -0.0366 0.7078 1.0000
5.250 0.4862 0.04634 0.03803 -0.0335 0.6962 1.0000
5.500 0.4948 0.04657 0.03829 -0.0310 0.6855 1.0000
5.750 0.5341 0.04617 0.03796 -0.0323 0.6817 1.0000
6.000 0.5423 0.04650 0.03836 -0.0300 0.6703 1.0000
6.250 0.5563 0.04685 0.03877 -0.0285 0.6601 1.0000
6.500 0.5942 0.04631 0.03833 -0.0296 0.6556 1.0000
6.750 0.6069 0.04679 0.03888 -0.0281 0.6445 1.0000
7.000 0.6487 0.04600 0.03824 -0.0295 0.6412 1.0000
7.250 0.6602 0.04663 0.03896 -0.0280 0.6295 1.0000
7.500 0.7045 0.04554 0.03803 -0.0295 0.6267 1.0000
7.750 0.7172 0.04614 0.03873 -0.0281 0.6147 1.0000
8.000 0.7323 0.04671 0.03943 -0.0271 0.6036 1.0000
8.250 0.7758 0.04543 0.03839 -0.0282 0.6003 1.0000
8.500 0.7907 0.04601 0.03912 -0.0271 0.5886 1.0000
8.750 0.8387 0.04410 0.03747 -0.0283 0.5861 1.0000
9.000 0.9450 0.03171 0.02548 -0.0281 0.5632 1.0000
9.250 0.9799 0.02836 0.02198 -0.0252 0.4980 1.0000
9.500 0.9729 0.02911 0.02203 -0.0196 0.3897 1.0000
9.750 0.9528 0.03161 0.02365 -0.0142 0.2646 1.0000
10.000 0.9282 0.03515 0.02604 -0.0096 0.1198 1.0000
10.250 0.9174 0.03816 0.02847 -0.0063 0.0671 1.0000
10.500 0.9184 0.04030 0.03060 -0.0042 0.0579 1.0000
10.750 0.9215 0.04232 0.03274 -0.0023 0.0524 1.0000
11.000 0.9220 0.04457 0.03507 -0.0005 0.0495 1.0000
11.250 0.9230 0.04683 0.03740 0.0013 0.0473 1.0000
11.500 0.9320 0.04851 0.03923 0.0028 0.0456 1.0000
11.750 0.9474 0.04979 0.04056 0.0040 0.0435 1.0000
12.000 0.9673 0.05096 0.04169 0.0048 0.0400 1.0000
12.250 1.0722 0.05197 0.04250 0.0009 0.0372 1.0000
12.500 1.1324 0.05501 0.04585 -0.0016 0.0375 1.0000
12.750 1.1488 0.05706 0.04823 -0.0005 0.0382 1.0000
13.000 1.1599 0.05959 0.05127 0.0013 0.0398 1.0000
13.250 1.1558 0.06342 0.05571 0.0042 0.0419 1.0000
13.500 1.1544 0.06742 0.06012 0.0061 0.0434 1.0000
13.750 1.1517 0.07159 0.06460 0.0078 0.0450 1.0000
14.000 1.1408 0.07564 0.06894 0.0096 0.0455 1.0000
14.250 1.1375 0.08075 0.07426 0.0105 0.0469 1.0000
14.500 0.9850 0.07839 0.07261 0.0200 0.0459 1.0000
14.750 0.9652 0.08290 0.07735 0.0205 0.0466 1.0000
15.000 0.9730 0.08766 0.08227 0.0204 0.0487 1.0000
15.250 0.9325 0.09022 0.08511 0.0210 0.0490 1.0000
15.500 0.8931 0.09412 0.08930 0.0201 0.0495 1.0000
15.750 0.8549 0.09923 0.09465 0.0178 0.0497 1.0000
16.000 0.8187 0.10517 0.10077 0.0145 0.0498 1.0000
16.250 0.7821 0.11213 0.10792 0.0099 0.0498 1.0000
16.500 0.7406 0.12090 0.11686 0.0037 0.0500 1.0000
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Polar data table (+)
Polar graphs
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