HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Reynolds number: 200,000 Max Cl/Cd: 66.53 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq17-il-200000-n5.txt Download as CSV file: xf-hq17-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURE
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.0233 0.11290 0.10888 -0.1115 0.8771 0.0238
-12.750 -0.0193 0.10985 0.10581 -0.1128 0.8754 0.0250
-12.500 -0.0793 0.10977 0.10557 -0.1255 0.8961 0.0207
-12.000 -0.0630 0.10362 0.09934 -0.1265 0.8900 0.0193
-11.750 -0.0582 0.10035 0.09607 -0.1275 0.8871 0.0185
-11.500 -0.0570 0.09673 0.09247 -0.1287 0.8833 0.0181
-11.250 -0.0560 0.09304 0.08878 -0.1300 0.8798 0.0181
-11.000 -0.0551 0.08932 0.08505 -0.1314 0.8766 0.0177
-10.750 -0.0556 0.08538 0.08111 -0.1330 0.8736 0.0177
-10.500 -0.0581 0.08143 0.07720 -0.1344 0.8698 0.0176
-10.250 -0.0613 0.07735 0.07312 -0.1360 0.8661 0.0177
-10.000 -0.0660 0.07291 0.06869 -0.1381 0.8628 0.0182
-9.750 -0.0758 0.06752 0.06333 -0.1410 0.8591 0.0187
-9.500 -0.0896 0.06147 0.05730 -0.1452 0.8544 0.0186
-9.250 -0.1096 0.05595 0.05172 -0.1477 0.8499 0.0185
-9.000 -0.1310 0.05185 0.04752 -0.1472 0.8446 0.0187
-8.750 -0.1520 0.04896 0.04451 -0.1446 0.8391 0.0186
-8.500 -0.1666 0.04515 0.04043 -0.1424 0.8352 0.0190
-8.250 -0.1778 0.04174 0.03678 -0.1396 0.8297 0.0194
-8.000 -0.1818 0.03854 0.03324 -0.1371 0.8256 0.0195
-7.750 -0.1793 0.03551 0.02979 -0.1350 0.8226 0.0198
-7.500 -0.1725 0.03318 0.02708 -0.1329 0.8189 0.0202
-7.250 -0.1649 0.03077 0.02425 -0.1308 0.8148 0.0210
-7.000 -0.1498 0.02899 0.02230 -0.1299 0.8120 0.0220
-6.750 -0.1305 0.02766 0.02075 -0.1293 0.8098 0.0229
-6.500 -0.1095 0.02602 0.01881 -0.1286 0.8080 0.0234
-6.250 -0.0918 0.02480 0.01737 -0.1273 0.8041 0.0238
-6.000 -0.0704 0.02361 0.01597 -0.1265 0.8010 0.0244
-5.750 -0.0469 0.02252 0.01466 -0.1260 0.7985 0.0251
-5.500 -0.0219 0.02155 0.01349 -0.1257 0.7966 0.0259
-5.250 0.0043 0.02085 0.01263 -0.1256 0.7950 0.0274
-5.000 0.0262 0.02027 0.01195 -0.1247 0.7918 0.0282
-4.750 0.0480 0.01964 0.01126 -0.1238 0.7885 0.0286
-4.500 0.0715 0.01904 0.01058 -0.1232 0.7859 0.0290
-4.250 0.0947 0.01821 0.00970 -0.1227 0.7837 0.0298
-4.000 0.1190 0.01751 0.00897 -0.1223 0.7819 0.0311
-3.750 0.1398 0.01716 0.00859 -0.1214 0.7786 0.0323
-3.500 0.1610 0.01688 0.00829 -0.1205 0.7751 0.0340
-3.250 0.1853 0.01661 0.00796 -0.1201 0.7725 0.0371
-3.000 0.2113 0.01631 0.00757 -0.1200 0.7706 0.0396
-2.750 0.2379 0.01592 0.00712 -0.1200 0.7689 0.0442
-2.500 0.2608 0.01572 0.00691 -0.1194 0.7662 0.0543
-2.250 0.2802 0.01526 0.00682 -0.1185 0.7627 0.1362
-2.000 0.3026 0.01469 0.00663 -0.1181 0.7600 0.2491
-1.750 0.3128 0.01326 0.00679 -0.1152 0.7577 0.6492
-1.500 0.3321 0.01371 0.00747 -0.1121 0.7560 0.7681
-1.250 0.3521 0.01418 0.00792 -0.1099 0.7533 0.7957
-1.000 0.3678 0.01466 0.00836 -0.1073 0.7491 0.8163
-0.750 0.3898 0.01484 0.00848 -0.1058 0.7462 0.8267
-0.500 0.4138 0.01493 0.00851 -0.1047 0.7440 0.8361
0.000 0.4544 0.01517 0.00866 -0.1017 0.7370 0.8534
0.250 0.4784 0.01519 0.00861 -0.1013 0.7332 0.8573
0.500 0.5058 0.01510 0.00846 -0.1014 0.7307 0.8600
0.750 0.5364 0.01500 0.00828 -0.1021 0.7288 0.8627
1.000 0.5524 0.01518 0.00847 -0.1003 0.7239 0.8667
1.250 0.5783 0.01520 0.00844 -0.1003 0.7206 0.8698
1.500 0.6057 0.01511 0.00832 -0.1004 0.7182 0.8722
1.750 0.6361 0.01502 0.00819 -0.1011 0.7164 0.8746
2.000 0.6567 0.01513 0.00831 -0.1001 0.7126 0.8776
2.250 0.6782 0.01524 0.00842 -0.0993 0.7087 0.8806
2.500 0.7074 0.01523 0.00839 -0.1000 0.7060 0.8830
2.750 0.7389 0.01511 0.00825 -0.1009 0.7037 0.8845
3.000 0.7613 0.01516 0.00832 -0.1002 0.6998 0.8865
3.250 0.7755 0.01534 0.00856 -0.0980 0.6943 0.8896
3.500 0.8045 0.01528 0.00849 -0.0985 0.6910 0.8922
3.750 0.8280 0.01531 0.00855 -0.0980 0.6865 0.8952
4.000 0.8408 0.01543 0.00872 -0.0954 0.6800 0.8980
4.250 0.8746 0.01522 0.00852 -0.0967 0.6760 0.8993
4.500 0.8827 0.01534 0.00868 -0.0932 0.6683 0.9021
4.750 0.9190 0.01507 0.00840 -0.0949 0.6631 0.9034
5.000 0.9273 0.01528 0.00867 -0.0916 0.6553 0.9069
5.250 0.9546 0.01526 0.00870 -0.0918 0.6505 0.9088
5.500 0.9636 0.01557 0.00908 -0.0888 0.6425 0.9116
5.750 0.9850 0.01560 0.00915 -0.0879 0.6354 0.9139
6.000 0.9915 0.01602 0.00966 -0.0845 0.6259 0.9177
6.250 1.0148 0.01608 0.00977 -0.0841 0.6189 0.9200
6.500 1.0357 0.01620 0.00995 -0.0832 0.6102 0.9225
6.750 1.0564 0.01637 0.01017 -0.0824 0.6019 0.9252
7.000 1.0845 0.01630 0.01012 -0.0826 0.5932 0.9274
7.250 1.0994 0.01666 0.01055 -0.0809 0.5818 0.9306
7.500 1.1158 0.01703 0.01099 -0.0795 0.5699 0.9339
7.750 1.1307 0.01746 0.01149 -0.0780 0.5542 0.9379
8.000 1.1430 0.01792 0.01186 -0.0760 0.5189 0.9436
8.250 1.1522 0.01873 0.01243 -0.0738 0.4719 0.9514
8.500 1.1535 0.01997 0.01342 -0.0709 0.4201 0.9881
9.000 1.1392 0.02343 0.01633 -0.0628 0.3357 1.0000
9.250 1.1326 0.02543 0.01807 -0.0594 0.2873 1.0000
9.500 1.1276 0.02747 0.01986 -0.0563 0.2487 1.0000
9.750 1.1299 0.02917 0.02142 -0.0543 0.2190 1.0000
10.000 1.1286 0.03119 0.02324 -0.0520 0.1753 1.0000
10.250 1.1271 0.03334 0.02512 -0.0498 0.1379 1.0000
10.500 1.1299 0.03524 0.02686 -0.0482 0.1044 1.0000
10.750 1.1337 0.03712 0.02859 -0.0467 0.0815 1.0000
11.000 1.1419 0.03870 0.03014 -0.0456 0.0676 1.0000
11.250 1.1511 0.04024 0.03169 -0.0447 0.0608 1.0000
11.500 1.1623 0.04164 0.03315 -0.0439 0.0551 1.0000
11.750 1.1686 0.04349 0.03495 -0.0429 0.0367 1.0000
12.000 1.1728 0.04557 0.03695 -0.0418 0.0214 1.0000
12.250 1.1766 0.04775 0.03915 -0.0407 0.0143 1.0000
12.500 1.1842 0.04963 0.04111 -0.0400 0.0100 1.0000
12.750 1.1907 0.05163 0.04317 -0.0392 0.0082 1.0000
13.000 1.1976 0.05364 0.04527 -0.0385 0.0074 1.0000
13.250 1.2043 0.05571 0.04742 -0.0379 0.0070 1.0000
13.500 1.2117 0.05773 0.04956 -0.0374 0.0068 1.0000
13.750 1.2164 0.06011 0.05205 -0.0368 0.0064 1.0000
14.000 1.2223 0.06238 0.05446 -0.0364 0.0062 1.0000
14.250 1.2271 0.06481 0.05703 -0.0361 0.0061 1.0000
14.500 1.2309 0.06742 0.05978 -0.0358 0.0060 1.0000
14.750 1.2337 0.07022 0.06271 -0.0356 0.0058 1.0000
15.000 1.2358 0.07313 0.06580 -0.0355 0.0057 1.0000
15.250 1.2364 0.07630 0.06911 -0.0355 0.0056 1.0000
15.500 1.2374 0.07947 0.07242 -0.0356 0.0055 1.0000
15.750 1.2370 0.08288 0.07598 -0.0358 0.0055 1.0000
16.000 1.2366 0.08636 0.07960 -0.0362 0.0054 1.0000
16.250 1.2357 0.08998 0.08335 -0.0367 0.0054 1.0000
16.500 1.2334 0.09384 0.08736 -0.0373 0.0053 1.0000
16.750 1.2318 0.09767 0.09132 -0.0381 0.0053 1.0000
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