HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 200,000 Max Cl/Cd: 59.94 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1511-il-200000-n5.txt Download as CSV file: xf-hq1511-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/11 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6675 0.06425 0.06052 -0.0446 1.0000 0.0118
-11.000 -0.6959 0.05565 0.05174 -0.0516 1.0000 0.0115
-10.750 -0.7214 0.04962 0.04552 -0.0551 1.0000 0.0115
-10.500 -0.7428 0.04535 0.04104 -0.0558 1.0000 0.0114
-10.250 -0.7622 0.04180 0.03723 -0.0539 1.0000 0.0114
-10.000 -0.7717 0.03820 0.03327 -0.0522 1.0000 0.0115
-9.750 -0.7736 0.03496 0.02964 -0.0505 1.0000 0.0116
-9.500 -0.7694 0.03224 0.02657 -0.0487 1.0000 0.0117
-9.250 -0.7616 0.02984 0.02385 -0.0469 1.0000 0.0118
-9.000 -0.7512 0.02782 0.02155 -0.0450 1.0000 0.0119
-8.750 -0.7390 0.02616 0.01965 -0.0432 1.0000 0.0121
-8.500 -0.7261 0.02467 0.01796 -0.0413 1.0000 0.0123
-8.250 -0.7131 0.02344 0.01657 -0.0393 1.0000 0.0125
-8.000 -0.6946 0.02224 0.01527 -0.0385 0.9980 0.0130
-7.750 -0.6636 0.02109 0.01397 -0.0400 0.9915 0.0135
-7.500 -0.6319 0.02003 0.01278 -0.0415 0.9855 0.0143
-7.250 -0.6004 0.01900 0.01159 -0.0428 0.9795 0.0156
-7.000 -0.5686 0.01802 0.01051 -0.0442 0.9734 0.0172
-6.750 -0.5366 0.01723 0.00965 -0.0456 0.9675 0.0203
-6.500 -0.5054 0.01656 0.00893 -0.0467 0.9604 0.0253
-6.250 -0.4722 0.01606 0.00840 -0.0481 0.9548 0.0321
-6.000 -0.4422 0.01565 0.00797 -0.0489 0.9466 0.0390
-5.750 -0.4101 0.01527 0.00748 -0.0500 0.9404 0.0447
-5.500 -0.3817 0.01480 0.00700 -0.0504 0.9315 0.0502
-5.250 -0.3520 0.01444 0.00655 -0.0509 0.9239 0.0561
-5.000 -0.3240 0.01401 0.00613 -0.0512 0.9155 0.0643
-4.750 -0.2962 0.01364 0.00570 -0.0513 0.9076 0.0738
-4.500 -0.2685 0.01327 0.00529 -0.0514 0.8998 0.0841
-4.250 -0.2422 0.01284 0.00489 -0.0512 0.8916 0.1000
-4.000 -0.2162 0.01231 0.00451 -0.0511 0.8843 0.1349
-3.750 -0.1915 0.01175 0.00421 -0.0509 0.8765 0.2097
-3.500 -0.1663 0.01123 0.00391 -0.0506 0.8696 0.2744
-3.250 -0.1429 0.01062 0.00370 -0.0501 0.8615 0.3739
-3.000 -0.1183 0.01022 0.00356 -0.0495 0.8542 0.4617
-2.750 -0.0937 0.00998 0.00353 -0.0487 0.8455 0.5279
-2.500 -0.0680 0.00988 0.00352 -0.0480 0.8382 0.5811
-2.250 -0.0422 0.00984 0.00353 -0.0474 0.8292 0.6177
-2.000 -0.0160 0.00983 0.00352 -0.0467 0.8210 0.6483
-1.750 0.0102 0.00983 0.00349 -0.0461 0.8115 0.6714
-1.500 0.0370 0.00982 0.00344 -0.0456 0.8026 0.6852
-1.250 0.0641 0.00980 0.00337 -0.0452 0.7948 0.6966
-1.000 0.0909 0.00979 0.00335 -0.0449 0.7864 0.7093
-0.750 0.1179 0.00979 0.00331 -0.0444 0.7789 0.7224
-0.500 0.1448 0.00979 0.00328 -0.0441 0.7696 0.7339
-0.250 0.1717 0.00978 0.00325 -0.0437 0.7616 0.7436
0.000 0.1987 0.00977 0.00323 -0.0433 0.7527 0.7525
0.250 0.2258 0.00977 0.00321 -0.0430 0.7433 0.7618
0.500 0.2525 0.00976 0.00319 -0.0425 0.7335 0.7709
0.750 0.2792 0.00976 0.00319 -0.0421 0.7225 0.7807
1.000 0.3059 0.00976 0.00320 -0.0418 0.7123 0.7897
1.250 0.3327 0.00977 0.00320 -0.0414 0.7025 0.7981
1.500 0.3596 0.00979 0.00322 -0.0410 0.6912 0.8072
1.750 0.3859 0.00979 0.00325 -0.0405 0.6787 0.8159
2.000 0.4123 0.00981 0.00329 -0.0401 0.6661 0.8257
2.250 0.4385 0.00983 0.00334 -0.0396 0.6531 0.8375
2.500 0.4644 0.00984 0.00340 -0.0390 0.6395 0.8504
2.750 0.4903 0.00986 0.00347 -0.0384 0.6243 0.8644
3.000 0.5164 0.00989 0.00354 -0.0378 0.6070 0.8790
3.250 0.5430 0.00994 0.00360 -0.0374 0.5869 0.8951
3.500 0.5710 0.01002 0.00368 -0.0373 0.5605 0.9145
3.750 0.6014 0.01018 0.00376 -0.0377 0.5220 0.9377
4.000 0.6336 0.01057 0.00387 -0.0389 0.4630 0.9674
4.250 0.6621 0.01106 0.00410 -0.0394 0.4112 1.0000
4.500 0.6847 0.01147 0.00437 -0.0387 0.3682 1.0000
4.750 0.7068 0.01195 0.00465 -0.0379 0.3266 1.0000
5.000 0.7295 0.01242 0.00497 -0.0373 0.2988 1.0000
5.500 0.7762 0.01327 0.00570 -0.0361 0.2599 1.0000
5.750 0.7998 0.01367 0.00608 -0.0356 0.2429 1.0000
6.000 0.8230 0.01412 0.00647 -0.0350 0.2234 1.0000
6.250 0.8457 0.01459 0.00689 -0.0344 0.2016 1.0000
6.500 0.8689 0.01502 0.00727 -0.0338 0.1707 1.0000
6.750 0.8894 0.01570 0.00772 -0.0329 0.1322 1.0000
7.000 0.9095 0.01644 0.00832 -0.0320 0.1071 1.0000
7.250 0.9304 0.01711 0.00894 -0.0312 0.0892 1.0000
7.500 0.9511 0.01778 0.00959 -0.0303 0.0743 1.0000
7.750 0.9713 0.01848 0.01027 -0.0294 0.0614 1.0000
8.000 0.9911 0.01921 0.01099 -0.0284 0.0511 1.0000
8.250 1.0099 0.02000 0.01179 -0.0272 0.0438 1.0000
8.500 1.0283 0.02079 0.01262 -0.0261 0.0382 1.0000
8.750 1.0453 0.02166 0.01354 -0.0247 0.0343 1.0000
9.000 1.0625 0.02248 0.01444 -0.0234 0.0312 1.0000
9.250 1.0770 0.02347 0.01547 -0.0218 0.0290 1.0000
9.500 1.0894 0.02458 0.01665 -0.0199 0.0274 1.0000
9.750 1.1023 0.02549 0.01769 -0.0180 0.0259 1.0000
10.000 1.1139 0.02648 0.01877 -0.0160 0.0243 1.0000
10.250 1.1245 0.02753 0.01991 -0.0141 0.0231 1.0000
10.500 1.1323 0.02881 0.02126 -0.0121 0.0221 1.0000
10.750 1.1375 0.03045 0.02296 -0.0099 0.0213 1.0000
11.000 1.1469 0.03180 0.02447 -0.0083 0.0206 1.0000
11.250 1.1552 0.03330 0.02612 -0.0067 0.0199 1.0000
11.500 1.1630 0.03485 0.02781 -0.0053 0.0191 1.0000
11.750 1.1697 0.03649 0.02958 -0.0040 0.0184 1.0000
12.000 1.1756 0.03819 0.03139 -0.0029 0.0176 1.0000
12.250 1.1799 0.04007 0.03338 -0.0019 0.0170 1.0000
12.500 1.1825 0.04226 0.03567 -0.0010 0.0166 1.0000
12.750 1.1824 0.04500 0.03851 -0.0001 0.0161 1.0000
13.000 1.1838 0.04754 0.04125 0.0004 0.0158 1.0000
13.250 1.1834 0.05038 0.04430 0.0008 0.0156 1.0000
13.500 1.1809 0.05355 0.04769 0.0008 0.0152 1.0000
13.750 1.1764 0.05702 0.05138 0.0005 0.0149 1.0000
14.000 1.1700 0.06090 0.05547 -0.0003 0.0146 1.0000
14.250 1.1619 0.06519 0.05996 -0.0015 0.0143 1.0000
14.500 1.1530 0.06977 0.06474 -0.0033 0.0140 1.0000
14.750 1.1415 0.07507 0.07024 -0.0056 0.0139 1.0000
15.000 1.1286 0.08097 0.07632 -0.0086 0.0137 1.0000
15.250 1.1161 0.08718 0.08271 -0.0122 0.0135 1.0000
15.500 1.0991 0.09469 0.09042 -0.0166 0.0135 1.0000
15.750 1.0808 0.10296 0.09888 -0.0216 0.0134 1.0000
16.000 1.0535 0.11387 0.11003 -0.0284 0.0137 1.0000
16.250 1.0189 0.12742 0.12381 -0.0369 0.0141 1.0000
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