AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 200,000 Max Cl/Cd: 69.76 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-7-il-200000-n5.txt Download as CSV file: xf-ah21-7-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5066 0.08853 0.08495 -0.0336 1.0000 0.0191
-9.000 -0.5173 0.08448 0.08094 -0.0341 1.0000 0.0189
-8.750 -0.5316 0.08035 0.07689 -0.0344 1.0000 0.0187
-8.500 -0.5513 0.07640 0.07301 -0.0345 1.0000 0.0185
-8.250 -0.5765 0.07152 0.06818 -0.0360 1.0000 0.0183
-8.000 -0.5904 0.06321 0.05977 -0.0412 0.9986 0.0178
-7.750 -0.5892 0.05183 0.04799 -0.0497 0.9936 0.0175
-7.500 -0.5837 0.04388 0.03956 -0.0530 0.9889 0.0176
-7.250 -0.5674 0.03880 0.03401 -0.0550 0.9856 0.0183
-7.000 -0.5467 0.03436 0.02900 -0.0567 0.9834 0.0194
-6.750 -0.5301 0.03072 0.02482 -0.0563 0.9798 0.0197
-6.500 -0.5079 0.02775 0.02133 -0.0563 0.9770 0.0200
-6.250 -0.4825 0.02549 0.01859 -0.0566 0.9748 0.0204
-6.000 -0.4545 0.02378 0.01649 -0.0571 0.9731 0.0208
-5.750 -0.4257 0.02217 0.01459 -0.0578 0.9717 0.0215
-5.500 -0.3994 0.02105 0.01338 -0.0581 0.9697 0.0226
-5.250 -0.3755 0.02026 0.01250 -0.0576 0.9664 0.0237
-5.000 -0.3484 0.01932 0.01142 -0.0576 0.9638 0.0244
-4.750 -0.3197 0.01847 0.01047 -0.0580 0.9617 0.0251
-4.500 -0.2896 0.01771 0.00961 -0.0586 0.9599 0.0261
-4.250 -0.2586 0.01707 0.00889 -0.0595 0.9583 0.0272
-4.000 -0.2319 0.01654 0.00828 -0.0594 0.9554 0.0281
-3.750 -0.2071 0.01598 0.00771 -0.0591 0.9517 0.0307
-3.500 -0.1778 0.01561 0.00731 -0.0595 0.9489 0.0339
-3.250 -0.1466 0.01521 0.00684 -0.0603 0.9466 0.0376
-3.000 -0.1140 0.01480 0.00641 -0.0614 0.9448 0.0476
-2.750 -0.0866 0.01436 0.00611 -0.0615 0.9416 0.0767
-2.500 -0.0616 0.01395 0.00591 -0.0613 0.9371 0.1277
-2.250 -0.0326 0.01331 0.00574 -0.0621 0.9342 0.2396
-2.000 -0.0031 0.01249 0.00566 -0.0630 0.9320 0.4224
-1.750 0.0277 0.01192 0.00563 -0.0638 0.9302 0.5620
-1.500 0.0461 0.01165 0.00567 -0.0616 0.9237 0.6516
-1.250 0.0724 0.01138 0.00569 -0.0608 0.9201 0.7414
-1.000 0.1016 0.01120 0.00567 -0.0605 0.9175 0.8093
-0.750 0.1248 0.01112 0.00568 -0.0590 0.9123 0.8589
-0.500 0.1523 0.01106 0.00565 -0.0584 0.9075 0.9015
-0.250 0.1912 0.01097 0.00556 -0.0603 0.9050 0.9363
0.000 0.2372 0.01086 0.00543 -0.0639 0.9033 0.9621
0.250 0.2852 0.01072 0.00526 -0.0681 0.9013 0.9810
0.500 0.3210 0.01065 0.00517 -0.0698 0.8939 1.0000
0.750 0.3581 0.01041 0.00490 -0.0716 0.8893 1.0000
1.000 0.3816 0.01026 0.00474 -0.0705 0.8792 1.0000
1.250 0.4163 0.01003 0.00449 -0.0716 0.8710 1.0000
1.500 0.4500 0.00981 0.00428 -0.0726 0.8604 1.0000
1.750 0.4816 0.00963 0.00409 -0.0731 0.8464 1.0000
2.000 0.5143 0.00946 0.00391 -0.0737 0.8294 1.0000
2.250 0.5491 0.00930 0.00375 -0.0748 0.8069 1.0000
2.500 0.5906 0.00916 0.00354 -0.0773 0.7750 1.0000
2.750 0.6285 0.00916 0.00337 -0.0790 0.7253 1.0000
3.000 0.6564 0.00941 0.00333 -0.0786 0.6592 1.0000
3.250 0.6740 0.00988 0.00342 -0.0762 0.5848 1.0000
3.500 0.6873 0.01046 0.00361 -0.0732 0.5082 1.0000
3.750 0.7003 0.01109 0.00387 -0.0703 0.4337 1.0000
4.000 0.7146 0.01175 0.00418 -0.0677 0.3637 1.0000
4.250 0.7308 0.01239 0.00453 -0.0656 0.2998 1.0000
4.500 0.7486 0.01302 0.00489 -0.0639 0.2447 1.0000
4.750 0.7678 0.01361 0.00526 -0.0625 0.1998 1.0000
5.000 0.7877 0.01419 0.00566 -0.0612 0.1633 1.0000
5.250 0.8083 0.01473 0.00608 -0.0600 0.1347 1.0000
5.500 0.8294 0.01525 0.00651 -0.0589 0.1132 1.0000
5.750 0.8504 0.01578 0.00697 -0.0578 0.0955 1.0000
6.000 0.8717 0.01629 0.00745 -0.0567 0.0828 1.0000
6.250 0.8928 0.01682 0.00797 -0.0556 0.0735 1.0000
6.500 0.9132 0.01741 0.00856 -0.0544 0.0652 1.0000
6.750 0.9344 0.01793 0.00913 -0.0533 0.0586 1.0000
7.000 0.9538 0.01862 0.00981 -0.0520 0.0536 1.0000
7.250 0.9744 0.01919 0.01047 -0.0508 0.0495 1.0000
7.500 0.9942 0.01983 0.01115 -0.0496 0.0454 1.0000
7.750 1.0124 0.02064 0.01199 -0.0481 0.0423 1.0000
8.000 1.0317 0.02134 0.01281 -0.0467 0.0400 1.0000
8.250 1.0503 0.02209 0.01365 -0.0452 0.0377 1.0000
8.500 1.0681 0.02286 0.01447 -0.0437 0.0356 1.0000
8.750 1.0834 0.02402 0.01566 -0.0419 0.0335 1.0000
9.000 1.1023 0.02480 0.01660 -0.0406 0.0320 1.0000
9.250 1.1201 0.02578 0.01773 -0.0391 0.0305 1.0000
9.500 1.1373 0.02681 0.01888 -0.0376 0.0291 1.0000
9.750 1.1535 0.02780 0.01998 -0.0360 0.0279 1.0000
10.000 1.1679 0.02882 0.02106 -0.0343 0.0265 1.0000
10.250 1.1816 0.03035 0.02269 -0.0326 0.0252 1.0000
10.500 1.1963 0.03161 0.02420 -0.0309 0.0243 1.0000
10.750 1.2091 0.03298 0.02581 -0.0290 0.0232 1.0000
11.000 1.2200 0.03428 0.02729 -0.0269 0.0221 1.0000
11.250 1.2293 0.03541 0.02856 -0.0247 0.0211 1.0000
11.500 1.2372 0.03654 0.02979 -0.0225 0.0202 1.0000
11.750 1.2425 0.03808 0.03142 -0.0203 0.0195 1.0000
12.000 1.2449 0.04021 0.03377 -0.0179 0.0188 1.0000
12.250 1.2463 0.04228 0.03615 -0.0154 0.0182 1.0000
12.500 1.2451 0.04451 0.03868 -0.0131 0.0174 1.0000
12.750 1.2428 0.04678 0.04119 -0.0111 0.0167 1.0000
13.000 1.2390 0.04924 0.04387 -0.0094 0.0162 1.0000
13.250 1.2345 0.05184 0.04664 -0.0080 0.0157 1.0000
13.500 1.2275 0.05490 0.04988 -0.0071 0.0154 1.0000
13.750 1.2199 0.05818 0.05332 -0.0068 0.0151 1.0000
14.000 1.2105 0.06195 0.05724 -0.0071 0.0149 1.0000
14.250 1.1967 0.06674 0.06222 -0.0082 0.0148 1.0000
14.500 1.1807 0.07233 0.06801 -0.0104 0.0147 1.0000
14.750 1.1621 0.07901 0.07488 -0.0138 0.0146 1.0000
15.000 1.1307 0.08929 0.08546 -0.0201 0.0148 1.0000
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Polar data table (+)
Polar graphs
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