HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.54 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq17-il-1000000.txt Download as CSV file: xf-hq17-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0373 0.08344 0.08089 -0.1374 0.8374 0.0126
-10.500 -0.0770 0.06833 0.06581 -0.1429 0.8312 0.0109
-10.250 -0.1102 0.05837 0.05593 -0.1483 0.8275 0.0108
-10.000 -0.1041 0.05625 0.05379 -0.1506 0.8243 0.0111
-9.500 -0.3221 0.02770 0.02414 -0.1390 0.8109 0.0099
-9.250 -0.3176 0.02563 0.02177 -0.1367 0.8080 0.0101
-9.000 -0.3253 0.02176 0.01744 -0.1332 0.8048 0.0108
-8.750 -0.3038 0.02146 0.01710 -0.1328 0.8025 0.0111
-8.500 -0.2810 0.02131 0.01694 -0.1326 0.8001 0.0114
-8.250 -0.2578 0.02115 0.01676 -0.1324 0.7975 0.0118
-8.000 -0.2364 0.02051 0.01601 -0.1319 0.7949 0.0124
-7.750 -0.2158 0.01947 0.01478 -0.1312 0.7925 0.0132
-7.500 -0.1933 0.01872 0.01383 -0.1307 0.7900 0.0137
-7.250 -0.1675 0.01890 0.01395 -0.1305 0.7877 0.0141
-7.000 -0.1525 0.01572 0.01046 -0.1293 0.7850 0.0150
-6.750 -0.1277 0.01529 0.00999 -0.1292 0.7825 0.0156
-6.500 -0.1020 0.01503 0.00970 -0.1292 0.7801 0.0164
-6.250 -0.0764 0.01454 0.00912 -0.1292 0.7777 0.0171
-6.000 -0.0508 0.01394 0.00843 -0.1291 0.7753 0.0177
-5.750 -0.0253 0.01329 0.00771 -0.1289 0.7729 0.0182
-5.500 0.0008 0.01282 0.00717 -0.1288 0.7704 0.0188
-5.250 0.0277 0.01260 0.00690 -0.1289 0.7681 0.0192
-5.000 0.0505 0.01138 0.00559 -0.1283 0.7657 0.0203
-4.750 0.0752 0.01080 0.00494 -0.1280 0.7633 0.0208
-4.500 0.1005 0.01039 0.00450 -0.1278 0.7610 0.0214
-4.250 0.1262 0.01004 0.00414 -0.1277 0.7586 0.0220
-4.000 0.1523 0.00974 0.00381 -0.1277 0.7562 0.0227
-3.750 0.1787 0.00947 0.00350 -0.1277 0.7538 0.0234
-3.500 0.2056 0.00927 0.00326 -0.1277 0.7513 0.0246
-3.250 0.2330 0.00912 0.00305 -0.1279 0.7484 0.0257
-3.000 0.2598 0.00894 0.00286 -0.1280 0.7460 0.0263
-2.750 0.2865 0.00869 0.00257 -0.1280 0.7433 0.0281
-2.500 0.3137 0.00851 0.00238 -0.1281 0.7408 0.0315
-2.250 0.3412 0.00837 0.00224 -0.1282 0.7384 0.0384
-2.000 0.3657 0.00782 0.00208 -0.1282 0.7359 0.1633
-1.750 0.3889 0.00713 0.00197 -0.1281 0.7332 0.3527
-1.500 0.4093 0.00616 0.00183 -0.1275 0.7303 0.6193
-1.250 0.4338 0.00591 0.00191 -0.1270 0.7271 0.7273
-1.000 0.4614 0.00596 0.00197 -0.1270 0.7240 0.7583
-0.750 0.4895 0.00605 0.00204 -0.1271 0.7210 0.7757
-0.500 0.5169 0.00616 0.00216 -0.1271 0.7182 0.7890
-0.250 0.5447 0.00629 0.00227 -0.1272 0.7153 0.7989
0.000 0.5720 0.00644 0.00244 -0.1271 0.7126 0.8061
0.250 0.6001 0.00656 0.00252 -0.1273 0.7098 0.8118
0.500 0.6285 0.00668 0.00259 -0.1275 0.7068 0.8158
0.750 0.6551 0.00681 0.00276 -0.1273 0.7041 0.8204
1.000 0.6825 0.00689 0.00284 -0.1274 0.7010 0.8241
1.250 0.7104 0.00694 0.00288 -0.1277 0.6977 0.8268
1.500 0.7384 0.00700 0.00289 -0.1279 0.6943 0.8289
1.750 0.7656 0.00704 0.00294 -0.1280 0.6908 0.8305
2.000 0.7922 0.00707 0.00299 -0.1280 0.6870 0.8321
2.250 0.8188 0.00710 0.00302 -0.1280 0.6821 0.8337
2.500 0.8451 0.00716 0.00306 -0.1279 0.6766 0.8355
2.750 0.8711 0.00719 0.00310 -0.1278 0.6707 0.8376
3.000 0.8971 0.00727 0.00314 -0.1276 0.6649 0.8397
3.250 0.9233 0.00731 0.00320 -0.1276 0.6593 0.8415
3.500 0.9495 0.00737 0.00325 -0.1276 0.6539 0.8430
3.750 0.9747 0.00743 0.00330 -0.1273 0.6491 0.8443
4.000 1.0003 0.00745 0.00337 -0.1272 0.6437 0.8455
4.250 1.0245 0.00752 0.00344 -0.1267 0.6366 0.8467
4.500 1.0486 0.00757 0.00351 -0.1262 0.6280 0.8480
4.750 1.0703 0.00767 0.00360 -0.1252 0.6174 0.8497
5.000 1.0899 0.00782 0.00371 -0.1238 0.6063 0.8518
5.250 1.1084 0.00799 0.00385 -0.1222 0.5945 0.8537
5.500 1.1285 0.00813 0.00399 -0.1209 0.5846 0.8552
5.750 1.1416 0.00833 0.00415 -0.1182 0.5696 0.8568
6.000 1.1482 0.00859 0.00434 -0.1141 0.5463 0.8585
6.250 1.1436 0.00918 0.00477 -0.1081 0.5082 0.8604
6.500 1.1419 0.00986 0.00531 -0.1028 0.4756 0.8624
6.750 1.1364 0.01077 0.00603 -0.0971 0.4369 0.8647
7.000 1.1211 0.01216 0.00710 -0.0901 0.3770 0.8675
7.250 1.1266 0.01296 0.00779 -0.0869 0.3502 0.8691
7.500 1.1259 0.01408 0.00873 -0.0828 0.3147 0.8706
7.750 1.1245 0.01520 0.00966 -0.0787 0.2723 0.8726
8.000 1.1237 0.01641 0.01068 -0.0748 0.2368 0.8745
8.250 1.1258 0.01755 0.01166 -0.0716 0.2038 0.8762
8.500 1.1284 0.01874 0.01268 -0.0685 0.1677 0.8779
8.750 1.1320 0.01993 0.01372 -0.0657 0.1400 0.8797
9.000 1.1388 0.02101 0.01470 -0.0634 0.1177 0.8813
9.250 1.1377 0.02259 0.01605 -0.0602 0.0777 0.8828
9.500 1.1450 0.02375 0.01712 -0.0582 0.0621 0.8841
9.750 1.1562 0.02467 0.01802 -0.0566 0.0502 0.8858
10.000 1.1539 0.02650 0.01963 -0.0536 0.0187 0.8874
10.250 1.1666 0.02742 0.02056 -0.0524 0.0151 0.8887
10.500 1.1737 0.02877 0.02187 -0.0506 0.0061 0.8901
10.750 1.1874 0.02968 0.02281 -0.0496 0.0056 0.8915
11.000 1.1995 0.03073 0.02392 -0.0484 0.0050 0.8929
11.250 1.2132 0.03169 0.02492 -0.0475 0.0049 0.8942
11.500 1.2252 0.03280 0.02609 -0.0465 0.0048 0.8955
11.750 1.2371 0.03394 0.02729 -0.0454 0.0046 0.8968
12.000 1.2477 0.03520 0.02862 -0.0444 0.0044 0.8984
12.250 1.2581 0.03650 0.02999 -0.0433 0.0042 0.9001
12.500 1.2667 0.03796 0.03152 -0.0422 0.0040 0.9017
12.750 1.2732 0.03966 0.03331 -0.0409 0.0038 0.9032
13.000 1.2810 0.04129 0.03500 -0.0399 0.0038 0.9048
13.250 1.2798 0.04380 0.03765 -0.0382 0.0035 0.9063
13.500 1.2871 0.04557 0.03950 -0.0374 0.0035 0.9078
13.750 1.2929 0.04752 0.04153 -0.0365 0.0035 0.9093
14.000 1.2989 0.04952 0.04362 -0.0357 0.0034 0.9108
14.250 1.3038 0.05166 0.04585 -0.0349 0.0034 0.9129
14.500 1.3081 0.05390 0.04819 -0.0342 0.0034 0.9152
14.750 1.3106 0.05637 0.05075 -0.0336 0.0034 0.9177
15.000 1.3139 0.05886 0.05335 -0.0330 0.0033 0.9206
15.250 1.3163 0.06150 0.05610 -0.0327 0.0034 0.9241
15.500 1.3176 0.06446 0.05921 -0.0325 0.0033 0.9319
15.750 1.3227 0.06763 0.06251 -0.0333 0.0033 0.9387
16.000 1.3289 0.07118 0.06618 -0.0348 0.0033 0.9472
16.250 1.3333 0.07472 0.06985 -0.0362 0.0033 0.9673
16.500 1.3323 0.07741 0.07262 -0.0354 0.0033 1.0000
16.750 1.3315 0.08074 0.07604 -0.0354 0.0033 1.0000
17.000 1.3313 0.08407 0.07947 -0.0357 0.0033 1.0000
17.250 1.3303 0.08758 0.08309 -0.0360 0.0033 1.0000
17.500 1.3303 0.09102 0.08663 -0.0366 0.0033 1.0000
17.750 1.3297 0.09463 0.09034 -0.0372 0.0032 1.0000
18.000 1.3269 0.09853 0.09436 -0.0379 0.0032 1.0000
18.250 1.3260 0.10232 0.09825 -0.0390 0.0032 1.0000
18.500 1.3223 0.10650 0.10256 -0.0400 0.0032 1.0000
18.750 1.3184 0.11081 0.10699 -0.0413 0.0032 1.0000
19.000 1.3139 0.11527 0.11158 -0.0427 0.0032 1.0000
19.250 1.3091 0.11988 0.11631 -0.0445 0.0032 1.0000
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