HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 50,000 Max Cl/Cd: 39.53 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259b-il-50000-n5.txt Download as CSV file: xf-hq259b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4209 0.09935 0.09236 -0.0311 1.0000 0.1250
-8.500 -0.4355 0.09030 0.08334 -0.0395 1.0000 0.0631
-8.250 -0.4314 0.08694 0.08003 -0.0385 1.0000 0.0609
-8.000 -0.4363 0.08344 0.07663 -0.0391 1.0000 0.0595
-7.750 -0.4418 0.07934 0.07263 -0.0413 1.0000 0.0580
-7.500 -0.4479 0.07495 0.06830 -0.0438 1.0000 0.0568
-7.250 -0.4537 0.07077 0.06413 -0.0455 1.0000 0.0559
-7.000 -0.4581 0.06673 0.06005 -0.0467 1.0000 0.0554
-6.750 -0.4599 0.06288 0.05611 -0.0474 1.0000 0.0552
-6.500 -0.4585 0.05928 0.05237 -0.0477 1.0000 0.0555
-6.250 -0.4543 0.05560 0.04848 -0.0480 1.0000 0.0556
-6.000 -0.4467 0.05178 0.04437 -0.0484 1.0000 0.0553
-5.750 -0.4354 0.04788 0.04007 -0.0488 1.0000 0.0545
-5.500 -0.4207 0.04434 0.03610 -0.0490 1.0000 0.0542
-5.250 -0.4033 0.04118 0.03251 -0.0491 1.0000 0.0542
-5.000 -0.3845 0.03855 0.02951 -0.0490 1.0000 0.0553
-4.750 -0.3643 0.03637 0.02695 -0.0488 1.0000 0.0581
-4.500 -0.3422 0.03418 0.02427 -0.0485 1.0000 0.0604
-4.250 -0.3189 0.03210 0.02174 -0.0481 1.0000 0.0615
-4.000 -0.2951 0.03031 0.01952 -0.0475 1.0000 0.0628
-3.750 -0.2716 0.02880 0.01766 -0.0467 1.0000 0.0644
-3.500 -0.2499 0.02754 0.01640 -0.0461 1.0000 0.0687
-3.250 -0.2275 0.02659 0.01526 -0.0451 1.0000 0.0740
-3.000 -0.2050 0.02570 0.01412 -0.0439 1.0000 0.0777
-2.750 -0.1838 0.02476 0.01322 -0.0429 1.0000 0.0826
-2.500 -0.1572 0.02408 0.01241 -0.0430 0.9982 0.0937
-2.250 -0.1244 0.02334 0.01158 -0.0444 0.9944 0.1092
-2.000 -0.0912 0.02241 0.01079 -0.0463 0.9904 0.1478
-1.750 -0.0665 0.02005 0.01079 -0.0463 0.9881 0.6023
-1.500 -0.0514 0.02001 0.01114 -0.0419 0.9827 0.7696
-1.250 -0.0388 0.01970 0.01105 -0.0370 0.9762 0.8944
-1.000 0.0083 0.01963 0.01070 -0.0413 0.9707 1.0000
-0.750 0.0421 0.01987 0.01060 -0.0435 0.9647 1.0000
-0.500 0.0783 0.02017 0.01060 -0.0460 0.9586 1.0000
-0.250 0.1142 0.02048 0.01066 -0.0484 0.9518 1.0000
0.000 0.1532 0.02079 0.01075 -0.0511 0.9433 1.0000
0.250 0.1914 0.02102 0.01081 -0.0536 0.9322 1.0000
0.500 0.2317 0.02124 0.01087 -0.0562 0.9206 1.0000
0.750 0.2736 0.02141 0.01094 -0.0590 0.9097 1.0000
1.000 0.3124 0.02157 0.01102 -0.0612 0.8988 1.0000
1.250 0.3463 0.02173 0.01113 -0.0625 0.8872 1.0000
1.500 0.3820 0.02187 0.01126 -0.0641 0.8761 1.0000
1.750 0.4217 0.02196 0.01134 -0.0661 0.8659 1.0000
2.000 0.4581 0.02201 0.01143 -0.0675 0.8546 1.0000
2.250 0.4902 0.02209 0.01156 -0.0681 0.8415 1.0000
2.500 0.5229 0.02212 0.01166 -0.0686 0.8279 1.0000
2.750 0.5556 0.02211 0.01173 -0.0690 0.8136 1.0000
3.000 0.5882 0.02205 0.01179 -0.0693 0.7984 1.0000
3.250 0.6209 0.02194 0.01179 -0.0694 0.7823 1.0000
3.500 0.6513 0.02184 0.01181 -0.0691 0.7639 1.0000
3.750 0.6790 0.02177 0.01190 -0.0683 0.7423 1.0000
4.000 0.7090 0.02161 0.01187 -0.0677 0.7199 1.0000
4.250 0.7371 0.02148 0.01186 -0.0668 0.6935 1.0000
4.500 0.7619 0.02147 0.01197 -0.0655 0.6609 1.0000
4.750 0.7880 0.02142 0.01205 -0.0642 0.6236 1.0000
5.000 0.8152 0.02134 0.01195 -0.0629 0.5808 1.0000
5.250 0.8422 0.02142 0.01183 -0.0615 0.5332 1.0000
5.500 0.8654 0.02189 0.01208 -0.0600 0.4852 1.0000
5.750 0.8862 0.02261 0.01260 -0.0585 0.4412 1.0000
6.000 0.9056 0.02344 0.01329 -0.0570 0.4005 1.0000
6.250 0.9240 0.02430 0.01408 -0.0555 0.3617 1.0000
6.500 0.9416 0.02519 0.01495 -0.0539 0.3222 1.0000
6.750 0.9575 0.02617 0.01592 -0.0523 0.2789 1.0000
7.000 0.9722 0.02731 0.01693 -0.0505 0.2326 1.0000
7.250 0.9865 0.02870 0.01810 -0.0489 0.1906 1.0000
7.500 1.0007 0.03029 0.01943 -0.0474 0.1582 1.0000
7.750 1.0164 0.03192 0.02096 -0.0462 0.1333 1.0000
8.000 1.0331 0.03361 0.02262 -0.0450 0.1146 1.0000
8.250 1.0505 0.03536 0.02445 -0.0439 0.1006 1.0000
8.500 1.0680 0.03721 0.02631 -0.0428 0.0902 1.0000
8.750 1.0863 0.03903 0.02831 -0.0418 0.0809 1.0000
9.000 1.1079 0.04128 0.03073 -0.0410 0.0748 1.0000
9.250 1.1287 0.04360 0.03331 -0.0402 0.0696 1.0000
9.500 1.1470 0.04599 0.03572 -0.0396 0.0651 1.0000
9.750 1.1601 0.04864 0.03891 -0.0381 0.0609 1.0000
10.000 1.1728 0.05161 0.04225 -0.0368 0.0582 1.0000
10.250 1.1827 0.05463 0.04556 -0.0355 0.0561 1.0000
10.500 1.1918 0.05760 0.04864 -0.0343 0.0538 1.0000
10.750 1.1880 0.06107 0.05249 -0.0321 0.0524 1.0000
11.000 1.1760 0.06456 0.05641 -0.0295 0.0513 1.0000
11.250 1.1610 0.06840 0.06061 -0.0276 0.0505 1.0000
11.500 1.1435 0.07268 0.06520 -0.0265 0.0500 1.0000
11.750 1.1234 0.07758 0.07038 -0.0266 0.0498 1.0000
12.000 1.1006 0.08330 0.07633 -0.0280 0.0499 1.0000
12.250 1.0760 0.08998 0.08321 -0.0308 0.0503 1.0000
12.500 1.0504 0.09781 0.09119 -0.0352 0.0509 1.0000
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Polar data table (+)
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