HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Reynolds number: 500,000 Max Cl/Cd: 113.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq17-il-500000.txt Download as CSV file: xf-hq17-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0089 0.08623 0.08339 -0.1244 0.8626 0.0193
-11.250 -0.0370 0.08840 0.08543 -0.1390 0.8773 0.0193
-11.000 -0.0472 0.08252 0.07956 -0.1406 0.8742 0.0198
-10.750 -0.0401 0.08075 0.07778 -0.1405 0.8711 0.0204
-10.500 -0.0399 0.07740 0.07444 -0.1416 0.8674 0.0205
-10.250 -0.0323 0.07572 0.07274 -0.1419 0.8640 0.0214
-10.000 -0.0308 0.07268 0.06968 -0.1432 0.8607 0.0219
-9.750 -0.0364 0.06852 0.06555 -0.1449 0.8569 0.0218
-9.500 -0.0381 0.06523 0.06227 -0.1465 0.8528 0.0237
-9.250 -0.0572 0.05885 0.05588 -0.1509 0.8483 0.0224
-9.000 -0.0783 0.05422 0.05121 -0.1524 0.8437 0.0224
-8.750 -0.0989 0.05101 0.04795 -0.1509 0.8384 0.0225
-8.500 -0.1157 0.04840 0.04523 -0.1485 0.8342 0.0230
-8.250 -0.1234 0.04531 0.04199 -0.1467 0.8305 0.0244
-7.500 -0.1447 0.03397 0.02966 -0.1388 0.8191 0.0276
-7.250 -0.1291 0.03230 0.02798 -0.1382 0.8166 0.0285
-7.000 -0.1138 0.03095 0.02657 -0.1374 0.8136 0.0296
-6.750 -0.0982 0.02934 0.02479 -0.1363 0.8107 0.0314
-6.500 -0.0701 0.03120 0.02634 -0.1354 0.8083 0.0357
-6.250 -0.0708 0.02196 0.01619 -0.1318 0.8059 0.0275
-6.000 -0.0454 0.02113 0.01515 -0.1314 0.8040 0.0269
-5.750 -0.0222 0.02009 0.01397 -0.1308 0.8012 0.0266
-5.500 0.0013 0.01853 0.01224 -0.1302 0.7984 0.0267
-5.250 0.0250 0.01644 0.00999 -0.1298 0.7959 0.0277
-5.000 0.0507 0.01540 0.00887 -0.1296 0.7937 0.0283
-4.750 0.0767 0.01462 0.00801 -0.1294 0.7918 0.0287
-4.500 0.1028 0.01403 0.00736 -0.1293 0.7900 0.0294
-4.250 0.1262 0.01354 0.00687 -0.1288 0.7873 0.0301
-4.000 0.1505 0.01313 0.00645 -0.1284 0.7846 0.0313
-3.750 0.1757 0.01277 0.00605 -0.1281 0.7821 0.0329
-3.500 0.2015 0.01238 0.00561 -0.1280 0.7799 0.0340
-3.250 0.2283 0.01205 0.00522 -0.1280 0.7780 0.0352
-3.000 0.2552 0.01169 0.00478 -0.1281 0.7762 0.0370
-2.750 0.2792 0.01141 0.00451 -0.1276 0.7732 0.0410
-2.500 0.3051 0.01122 0.00430 -0.1275 0.7704 0.0475
-2.250 0.3265 0.01026 0.00404 -0.1271 0.7679 0.2320
-2.000 0.3423 0.00871 0.00379 -0.1261 0.7656 0.6183
-1.750 0.3661 0.00863 0.00406 -0.1250 0.7636 0.7408
-1.500 0.3928 0.00881 0.00422 -0.1246 0.7609 0.7722
-1.250 0.4173 0.00909 0.00453 -0.1237 0.7576 0.7906
-1.000 0.4425 0.00945 0.00487 -0.1228 0.7547 0.8064
-0.750 0.4689 0.00971 0.00510 -0.1222 0.7522 0.8174
-0.500 0.4962 0.00997 0.00530 -0.1218 0.7498 0.8285
-0.250 0.5210 0.01012 0.00544 -0.1210 0.7470 0.8326
0.000 0.5444 0.01024 0.00557 -0.1201 0.7433 0.8388
0.250 0.5686 0.01035 0.00567 -0.1192 0.7401 0.8461
0.500 0.5948 0.01040 0.00569 -0.1188 0.7374 0.8513
0.750 0.6250 0.01041 0.00563 -0.1196 0.7350 0.8551
1.000 0.6508 0.01043 0.00564 -0.1195 0.7317 0.8579
1.250 0.6753 0.01039 0.00562 -0.1191 0.7281 0.8601
1.500 0.7023 0.01036 0.00558 -0.1191 0.7250 0.8625
1.750 0.7313 0.01034 0.00552 -0.1196 0.7224 0.8651
2.000 0.7598 0.01037 0.00552 -0.1201 0.7196 0.8679
2.250 0.7858 0.01042 0.00560 -0.1201 0.7158 0.8707
2.500 0.8111 0.01035 0.00554 -0.1198 0.7123 0.8728
2.750 0.8389 0.01030 0.00547 -0.1200 0.7090 0.8750
3.000 0.8663 0.01031 0.00547 -0.1202 0.7052 0.8772
3.250 0.8896 0.01030 0.00550 -0.1196 0.6998 0.8796
3.500 0.9178 0.01025 0.00542 -0.1199 0.6944 0.8818
3.750 0.9437 0.01028 0.00546 -0.1199 0.6890 0.8839
4.000 0.9666 0.01020 0.00541 -0.1192 0.6832 0.8856
4.250 0.9939 0.01014 0.00533 -0.1193 0.6780 0.8872
4.500 1.0140 0.01013 0.00539 -0.1180 0.6716 0.8895
4.750 1.0393 0.01012 0.00539 -0.1178 0.6666 0.8918
5.000 1.0645 0.01017 0.00547 -0.1176 0.6618 0.8942
5.250 1.0866 0.01021 0.00556 -0.1168 0.6553 0.8963
5.500 1.1087 0.01022 0.00557 -0.1159 0.6466 0.8977
5.750 1.1265 0.01019 0.00558 -0.1142 0.6374 0.8997
6.000 1.1414 0.01020 0.00565 -0.1118 0.6264 0.9020
6.250 1.1586 0.01025 0.00572 -0.1100 0.6178 0.9040
6.500 1.1717 0.01032 0.00577 -0.1073 0.6069 0.9061
6.750 1.1825 0.01052 0.00593 -0.1042 0.5930 0.9084
7.000 1.1893 0.01084 0.00623 -0.1005 0.5749 0.9109
7.250 1.1959 0.01113 0.00653 -0.0968 0.5562 0.9136
7.500 1.1958 0.01164 0.00697 -0.0920 0.5281 0.9165
7.750 1.1928 0.01238 0.00759 -0.0870 0.4979 0.9198
8.000 1.1834 0.01349 0.00850 -0.0812 0.4610 0.9236
8.250 1.1728 0.01485 0.00965 -0.0756 0.4134 0.9273
8.500 1.1649 0.01627 0.01088 -0.0708 0.3759 0.9314
8.750 1.1630 0.01760 0.01207 -0.0671 0.3426 0.9359
9.000 1.1659 0.01887 0.01323 -0.0643 0.3133 0.9400
9.250 1.1670 0.02052 0.01468 -0.0619 0.2689 0.9456
9.500 1.1742 0.02225 0.01625 -0.0608 0.2332 0.9524
9.750 1.1859 0.02389 0.01773 -0.0607 0.1936 0.9722
10.000 1.1814 0.02575 0.01934 -0.0574 0.1514 1.0000
10.250 1.1882 0.02719 0.02067 -0.0558 0.1293 1.0000
10.500 1.1866 0.02925 0.02246 -0.0534 0.0879 1.0000
10.750 1.1941 0.03074 0.02387 -0.0520 0.0714 1.0000
11.000 1.2011 0.03228 0.02534 -0.0506 0.0558 1.0000
11.250 1.2109 0.03368 0.02671 -0.0495 0.0440 1.0000
11.500 1.2100 0.03593 0.02877 -0.0476 0.0195 1.0000
11.750 1.2175 0.03758 0.03043 -0.0464 0.0130 1.0000
12.000 1.2256 0.03923 0.03211 -0.0453 0.0097 1.0000
12.250 1.2355 0.04074 0.03366 -0.0444 0.0086 1.0000
12.500 1.2444 0.04238 0.03536 -0.0436 0.0078 1.0000
12.750 1.2525 0.04412 0.03718 -0.0426 0.0074 1.0000
13.000 1.2613 0.04581 0.03896 -0.0419 0.0072 1.0000
13.250 1.2692 0.04763 0.04086 -0.0411 0.0069 1.0000
13.500 1.2758 0.04962 0.04295 -0.0403 0.0066 1.0000
13.750 1.2815 0.05172 0.04514 -0.0396 0.0065 1.0000
14.000 1.2857 0.05400 0.04752 -0.0389 0.0062 1.0000
14.250 1.2894 0.05640 0.05000 -0.0382 0.0061 1.0000
14.500 1.2923 0.05894 0.05264 -0.0376 0.0060 1.0000
14.750 1.2956 0.06150 0.05530 -0.0371 0.0061 1.0000
15.000 1.2938 0.06467 0.05856 -0.0366 0.0057 1.0000
15.250 1.2964 0.06740 0.06139 -0.0363 0.0058 1.0000
15.500 1.2937 0.07082 0.06491 -0.0360 0.0056 1.0000
15.750 1.2938 0.07397 0.06816 -0.0359 0.0056 1.0000
16.000 1.2919 0.07742 0.07172 -0.0357 0.0055 1.0000
16.250 1.2929 0.08053 0.07493 -0.0358 0.0055 1.0000
16.500 1.2934 0.08376 0.07828 -0.0359 0.0055 1.0000
16.750 1.2925 0.08719 0.08181 -0.0360 0.0055 1.0000
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