HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 100,000 Max Cl/Cd: 56.75 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2511-il-100000.txt Download as CSV file: xf-hq2511-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3922 0.10117 0.09625 -0.0370 1.0000 0.0965
-9.250 -0.4194 0.09816 0.09342 -0.0435 1.0000 0.0992
-9.000 -0.4455 0.09462 0.09004 -0.0484 1.0000 0.0995
-8.750 -0.4009 0.09038 0.08570 -0.0405 1.0000 0.1030
-8.500 -0.3974 0.08756 0.08293 -0.0398 1.0000 0.1062
-8.250 -0.4058 0.08456 0.08003 -0.0404 1.0000 0.1096
-8.000 -0.4304 0.08188 0.07750 -0.0413 1.0000 0.1120
-7.750 -0.4720 0.07896 0.07472 -0.0436 1.0000 0.1131
-7.500 -0.5126 0.07719 0.07288 -0.0439 1.0000 0.1139
-7.250 -0.5075 0.07291 0.06876 -0.0410 1.0000 0.1157
-7.000 -0.5004 0.07080 0.06672 -0.0372 1.0000 0.1181
-6.750 -0.5066 0.06845 0.06440 -0.0353 1.0000 0.1206
-6.500 -0.5350 0.06498 0.06057 -0.0386 1.0000 0.1295
-6.250 -0.5257 0.06182 0.05759 -0.0357 1.0000 0.1317
-6.000 -0.5226 0.04877 0.04317 -0.0411 1.0000 0.0723
-5.750 -0.5072 0.04229 0.03627 -0.0405 1.0000 0.0557
-5.500 -0.4923 0.03848 0.03209 -0.0401 1.0000 0.0535
-5.250 -0.4738 0.03535 0.02849 -0.0398 1.0000 0.0536
-5.000 -0.4529 0.03271 0.02532 -0.0394 1.0000 0.0551
-4.750 -0.4302 0.03038 0.02244 -0.0388 1.0000 0.0567
-4.500 -0.4066 0.02817 0.01971 -0.0381 1.0000 0.0585
-4.250 -0.3782 0.02588 0.01734 -0.0388 0.9983 0.0647
-4.000 -0.3410 0.02407 0.01524 -0.0406 0.9945 0.0821
-3.750 -0.3073 0.02307 0.01422 -0.0425 0.9897 0.1038
-3.500 -0.2718 0.02236 0.01352 -0.0447 0.9852 0.1234
-3.250 -0.2381 0.02152 0.01272 -0.0460 0.9804 0.1357
-3.000 -0.2048 0.02093 0.01218 -0.0474 0.9750 0.1556
-2.750 -0.1667 0.02026 0.01178 -0.0498 0.9705 0.1940
-2.500 -0.1470 0.01825 0.01193 -0.0486 0.9641 0.6045
-2.250 -0.1146 0.01883 0.01258 -0.0480 0.9566 0.7160
-2.000 -0.0920 0.01908 0.01281 -0.0461 0.9468 0.7624
-1.750 -0.0653 0.01934 0.01304 -0.0449 0.9394 0.8005
-1.500 -0.0452 0.01947 0.01314 -0.0425 0.9315 0.8387
-1.250 -0.0249 0.01956 0.01321 -0.0400 0.9249 0.8770
-1.000 -0.0025 0.01956 0.01323 -0.0377 0.9176 0.9251
-0.750 0.0751 0.01984 0.01337 -0.0466 0.9155 0.9707
-0.500 0.1536 0.02002 0.01335 -0.0567 0.9133 0.9868
-0.250 0.1865 0.02007 0.01331 -0.0594 0.9041 1.0000
0.000 0.2102 0.02012 0.01326 -0.0600 0.8956 1.0000
0.250 0.2379 0.02019 0.01325 -0.0612 0.8869 1.0000
0.500 0.2634 0.02037 0.01334 -0.0618 0.8771 1.0000
0.750 0.3099 0.02039 0.01329 -0.0657 0.8711 1.0000
1.000 0.3403 0.02050 0.01334 -0.0667 0.8600 1.0000
1.250 0.3888 0.02026 0.01306 -0.0702 0.8514 1.0000
1.500 0.4342 0.01990 0.01267 -0.0728 0.8420 1.0000
1.750 0.4656 0.01984 0.01258 -0.0733 0.8302 1.0000
2.000 0.5022 0.01967 0.01241 -0.0745 0.8210 1.0000
2.250 0.5412 0.01933 0.01208 -0.0758 0.8122 1.0000
2.500 0.5704 0.01923 0.01199 -0.0756 0.7999 1.0000
2.750 0.6014 0.01905 0.01183 -0.0756 0.7883 1.0000
3.000 0.6357 0.01871 0.01153 -0.0759 0.7779 1.0000
3.250 0.6696 0.01833 0.01117 -0.0760 0.7672 1.0000
3.500 0.6986 0.01808 0.01095 -0.0754 0.7532 1.0000
3.750 0.7286 0.01769 0.01061 -0.0747 0.7383 1.0000
4.000 0.7579 0.01727 0.01021 -0.0738 0.7215 1.0000
4.250 0.7832 0.01702 0.00999 -0.0725 0.7009 1.0000
4.500 0.8119 0.01665 0.00964 -0.0715 0.6809 1.0000
4.750 0.8373 0.01646 0.00948 -0.0703 0.6573 1.0000
5.000 0.8634 0.01628 0.00930 -0.0691 0.6320 1.0000
5.250 0.8874 0.01622 0.00925 -0.0677 0.6016 1.0000
5.500 0.9104 0.01625 0.00924 -0.0662 0.5660 1.0000
5.750 0.9324 0.01643 0.00930 -0.0646 0.5253 1.0000
6.000 0.9532 0.01685 0.00951 -0.0630 0.4823 1.0000
6.250 0.9730 0.01753 0.00996 -0.0614 0.4406 1.0000
6.500 0.9920 0.01834 0.01054 -0.0598 0.4009 1.0000
6.750 1.0100 0.01912 0.01120 -0.0581 0.3625 1.0000
7.000 1.0284 0.02002 0.01190 -0.0566 0.3303 1.0000
7.250 1.0481 0.02109 0.01280 -0.0554 0.3025 1.0000
7.500 1.0685 0.02221 0.01384 -0.0544 0.2781 1.0000
7.750 1.0870 0.02315 0.01465 -0.0532 0.2558 1.0000
8.000 1.1027 0.02384 0.01542 -0.0515 0.2339 1.0000
8.250 1.1188 0.02454 0.01613 -0.0500 0.2155 1.0000
8.500 1.1332 0.02524 0.01681 -0.0483 0.1978 1.0000
8.750 1.1458 0.02585 0.01762 -0.0463 0.1787 1.0000
9.000 1.1559 0.02655 0.01840 -0.0440 0.1582 1.0000
9.250 1.1589 0.02758 0.01938 -0.0409 0.1287 1.0000
9.500 1.1555 0.02954 0.02112 -0.0371 0.0904 1.0000
9.750 1.1572 0.03164 0.02310 -0.0340 0.0733 1.0000
10.000 1.1618 0.03357 0.02495 -0.0315 0.0648 1.0000
10.250 1.1720 0.03530 0.02681 -0.0296 0.0583 1.0000
10.500 1.1791 0.03737 0.02877 -0.0278 0.0536 1.0000
10.750 1.1945 0.03934 0.03099 -0.0264 0.0506 1.0000
11.000 1.2112 0.04153 0.03333 -0.0252 0.0480 1.0000
11.250 1.2284 0.04388 0.03580 -0.0243 0.0461 1.0000
11.500 1.2499 0.04695 0.03891 -0.0240 0.0440 1.0000
11.750 1.2603 0.05034 0.04259 -0.0228 0.0428 1.0000
12.000 1.2592 0.05315 0.04576 -0.0206 0.0419 1.0000
12.250 1.2547 0.05632 0.04928 -0.0187 0.0412 1.0000
12.500 1.2476 0.05994 0.05323 -0.0171 0.0410 1.0000
12.750 1.2360 0.06397 0.05758 -0.0159 0.0409 1.0000
13.000 1.2212 0.06834 0.06226 -0.0152 0.0410 1.0000
13.250 1.2031 0.07317 0.06738 -0.0152 0.0411 1.0000
13.500 1.1828 0.07856 0.07303 -0.0161 0.0414 1.0000
13.750 1.1609 0.08449 0.07920 -0.0179 0.0416 1.0000
14.000 1.1374 0.09112 0.08604 -0.0207 0.0419 1.0000
14.250 1.1127 0.09853 0.09364 -0.0246 0.0422 1.0000
14.500 1.0877 0.10679 0.10207 -0.0295 0.0426 1.0000
14.750 1.0642 0.11570 0.11110 -0.0350 0.0431 1.0000
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