HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il) Reynolds number: 200,000 Max Cl/Cd: 61.82 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3518-il-200000-n5.txt Download as CSV file: xf-hq3518-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/18 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6659 0.07760 0.07281 -0.0897 1.0000 0.0356
-15.750 -0.7043 0.06873 0.06367 -0.0950 1.0000 0.0357
-15.500 -0.7335 0.06226 0.05696 -0.0983 1.0000 0.0360
-15.250 -0.7520 0.05783 0.05236 -0.0998 1.0000 0.0362
-15.000 -0.7566 0.05532 0.04983 -0.1000 1.0000 0.0365
-14.750 -0.7621 0.05299 0.04747 -0.0999 1.0000 0.0368
-14.500 -0.7692 0.05092 0.04538 -0.0992 1.0000 0.0371
-14.250 -0.7663 0.04844 0.04284 -0.1005 0.9963 0.0376
-14.000 -0.7554 0.04576 0.04004 -0.1034 0.9861 0.0381
-13.750 -0.7428 0.04312 0.03724 -0.1066 0.9794 0.0388
-13.500 -0.7293 0.04060 0.03454 -0.1095 0.9722 0.0396
-13.250 -0.7136 0.03820 0.03190 -0.1124 0.9656 0.0406
-13.000 -0.6973 0.03595 0.02939 -0.1150 0.9576 0.0415
-12.750 -0.6757 0.03445 0.02786 -0.1170 0.9497 0.0423
-12.500 -0.6529 0.03310 0.02646 -0.1191 0.9414 0.0431
-12.250 -0.6340 0.03183 0.02509 -0.1202 0.9308 0.0440
-12.000 -0.6144 0.03058 0.02372 -0.1212 0.9210 0.0450
-11.750 -0.5962 0.02940 0.02239 -0.1217 0.9108 0.0461
-11.500 -0.5798 0.02831 0.02111 -0.1216 0.9007 0.0473
-11.250 -0.5613 0.02730 0.02002 -0.1216 0.8923 0.0483
-11.000 -0.5465 0.02650 0.01917 -0.1209 0.8829 0.0493
-10.750 -0.5306 0.02573 0.01832 -0.1202 0.8750 0.0504
-10.500 -0.5166 0.02501 0.01751 -0.1190 0.8666 0.0516
-10.250 -0.5004 0.02430 0.01667 -0.1179 0.8603 0.0529
-10.000 -0.4872 0.02373 0.01597 -0.1163 0.8525 0.0542
-9.750 -0.4727 0.02313 0.01533 -0.1148 0.8463 0.0556
-9.500 -0.4573 0.02263 0.01479 -0.1134 0.8400 0.0569
-9.250 -0.4406 0.02216 0.01429 -0.1122 0.8333 0.0586
-9.000 -0.4217 0.02166 0.01368 -0.1112 0.8281 0.0604
-8.750 -0.4034 0.02120 0.01313 -0.1100 0.8219 0.0622
-8.500 -0.3857 0.02067 0.01261 -0.1088 0.8161 0.0641
-8.250 -0.3658 0.02024 0.01214 -0.1080 0.8116 0.0661
-8.000 -0.3456 0.01986 0.01171 -0.1071 0.8068 0.0686
-7.750 -0.3251 0.01948 0.01126 -0.1061 0.8013 0.0711
-7.500 -0.3052 0.01900 0.01077 -0.1052 0.7965 0.0736
-7.250 -0.2834 0.01860 0.01032 -0.1045 0.7923 0.0764
-7.000 -0.2623 0.01827 0.00997 -0.1037 0.7865 0.0796
-6.750 -0.2401 0.01793 0.00956 -0.1029 0.7816 0.0828
-6.500 -0.2183 0.01747 0.00911 -0.1023 0.7777 0.0864
-6.250 -0.1949 0.01715 0.00873 -0.1017 0.7740 0.0906
-6.000 -0.1721 0.01687 0.00842 -0.1011 0.7692 0.0948
-5.750 -0.1500 0.01645 0.00801 -0.1004 0.7647 0.1000
-5.500 -0.1256 0.01614 0.00763 -0.1000 0.7606 0.1058
-5.250 -0.1016 0.01576 0.00724 -0.0996 0.7569 0.1129
-5.000 -0.0786 0.01544 0.00696 -0.0990 0.7522 0.1225
-4.750 -0.0556 0.01503 0.00669 -0.0986 0.7480 0.1422
-4.500 -0.0315 0.01464 0.00645 -0.0982 0.7442 0.1866
-4.250 -0.0057 0.01433 0.00617 -0.0981 0.7411 0.2155
-3.750 0.0417 0.01365 0.00580 -0.0973 0.7326 0.2934
-3.500 0.0655 0.01322 0.00557 -0.0969 0.7286 0.3438
-3.000 0.1171 0.01282 0.00555 -0.0963 0.7214 0.4889
-2.750 0.1428 0.01283 0.00559 -0.0959 0.7167 0.5111
-2.500 0.1695 0.01284 0.00561 -0.0956 0.7128 0.5301
-2.250 0.1971 0.01285 0.00561 -0.0955 0.7093 0.5436
-2.000 0.2256 0.01286 0.00558 -0.0955 0.7059 0.5548
-1.750 0.2528 0.01290 0.00557 -0.0953 0.7014 0.5658
-1.500 0.2785 0.01294 0.00566 -0.0948 0.6959 0.5767
-1.250 0.3060 0.01296 0.00565 -0.0946 0.6906 0.5876
-1.000 0.3350 0.01298 0.00561 -0.0947 0.6862 0.5966
-0.750 0.3603 0.01303 0.00568 -0.0942 0.6803 0.6042
-0.500 0.3869 0.01308 0.00573 -0.0938 0.6753 0.6109
-0.250 0.4152 0.01310 0.00568 -0.0939 0.6707 0.6182
0.000 0.4425 0.01313 0.00571 -0.0937 0.6660 0.6231
0.250 0.4679 0.01318 0.00578 -0.0933 0.6599 0.6279
0.500 0.4953 0.01319 0.00575 -0.0931 0.6542 0.6338
0.750 0.5229 0.01322 0.00574 -0.0930 0.6490 0.6398
1.000 0.5478 0.01329 0.00587 -0.0924 0.6427 0.6452
1.250 0.5746 0.01333 0.00589 -0.0922 0.6371 0.6517
1.500 0.6023 0.01336 0.00588 -0.0922 0.6320 0.6572
1.750 0.6264 0.01343 0.00601 -0.0915 0.6250 0.6618
2.000 0.6528 0.01346 0.00603 -0.0912 0.6184 0.6673
2.250 0.6781 0.01352 0.00607 -0.0908 0.6104 0.6738
2.500 0.7024 0.01355 0.00613 -0.0900 0.6012 0.6789
2.750 0.7266 0.01362 0.00621 -0.0893 0.5925 0.6855
3.000 0.7514 0.01369 0.00626 -0.0888 0.5838 0.6921
3.250 0.7745 0.01376 0.00636 -0.0879 0.5741 0.6970
3.500 0.7982 0.01383 0.00641 -0.0871 0.5638 0.7027
3.750 0.8203 0.01394 0.00650 -0.0861 0.5511 0.7089
4.000 0.8414 0.01404 0.00660 -0.0848 0.5373 0.7139
4.250 0.8616 0.01417 0.00671 -0.0834 0.5223 0.7197
4.500 0.8809 0.01435 0.00682 -0.0819 0.5066 0.7261
4.750 0.8984 0.01456 0.00697 -0.0800 0.4908 0.7316
5.000 0.9149 0.01480 0.00715 -0.0780 0.4772 0.7377
5.500 0.9446 0.01535 0.00761 -0.0735 0.4514 0.7504
5.750 0.9593 0.01568 0.00792 -0.0713 0.4393 0.7571
6.000 0.9745 0.01607 0.00825 -0.0693 0.4282 0.7644
6.250 0.9898 0.01639 0.00862 -0.0673 0.4174 0.7712
6.500 1.0039 0.01681 0.00901 -0.0652 0.4064 0.7793
6.750 1.0181 0.01718 0.00943 -0.0632 0.3936 0.7873
7.000 1.0323 0.01758 0.00987 -0.0612 0.3806 0.7962
7.250 1.0455 0.01803 0.01034 -0.0591 0.3655 0.8054
7.500 1.0568 0.01858 0.01087 -0.0569 0.3493 0.8161
7.750 1.0658 0.01924 0.01149 -0.0545 0.3348 0.8279
8.000 1.0746 0.01997 0.01218 -0.0521 0.3235 0.8423
8.250 1.0864 0.02062 0.01287 -0.0503 0.3138 0.8616
8.500 1.1015 0.02131 0.01363 -0.0492 0.3054 0.9005
8.750 1.1190 0.02191 0.01428 -0.0487 0.2975 1.0000
9.000 1.1312 0.02280 0.01510 -0.0473 0.2903 1.0000
9.250 1.1469 0.02351 0.01584 -0.0463 0.2831 1.0000
9.500 1.1599 0.02437 0.01668 -0.0451 0.2755 1.0000
9.750 1.1736 0.02522 0.01753 -0.0440 0.2684 1.0000
10.000 1.1876 0.02606 0.01839 -0.0429 0.2608 1.0000
10.250 1.1991 0.02705 0.01935 -0.0417 0.2538 1.0000
10.500 1.2137 0.02789 0.02025 -0.0408 0.2459 1.0000
10.750 1.2241 0.02898 0.02132 -0.0395 0.2384 1.0000
11.000 1.2372 0.02994 0.02234 -0.0386 0.2297 1.0000
11.250 1.2461 0.03118 0.02355 -0.0374 0.2218 1.0000
11.500 1.2580 0.03227 0.02468 -0.0365 0.2129 1.0000
11.750 1.2664 0.03362 0.02601 -0.0354 0.2058 1.0000
12.000 1.2772 0.03484 0.02727 -0.0344 0.1988 1.0000
12.250 1.2848 0.03631 0.02873 -0.0334 0.1930 1.0000
12.500 1.2948 0.03765 0.03010 -0.0326 0.1879 1.0000
12.750 1.3038 0.03909 0.03157 -0.0318 0.1830 1.0000
13.000 1.3111 0.04070 0.03317 -0.0309 0.1785 1.0000
13.250 1.3198 0.04222 0.03473 -0.0302 0.1744 1.0000
13.500 1.3295 0.04370 0.03626 -0.0295 0.1700 1.0000
13.750 1.3366 0.04543 0.03800 -0.0289 0.1658 1.0000
14.000 1.3431 0.04722 0.03978 -0.0282 0.1625 1.0000
14.250 1.3530 0.04876 0.04141 -0.0278 0.1591 1.0000
14.500 1.3620 0.05042 0.04315 -0.0274 0.1553 1.0000
14.750 1.3689 0.05228 0.04506 -0.0270 0.1517 1.0000
15.000 1.3746 0.05429 0.04706 -0.0266 0.1485 1.0000
15.250 1.3826 0.05610 0.04894 -0.0263 0.1455 1.0000
15.500 1.3911 0.05793 0.05090 -0.0261 0.1425 1.0000
15.750 1.3975 0.06000 0.05305 -0.0260 0.1390 1.0000
16.000 1.4021 0.06227 0.05537 -0.0259 0.1359 1.0000
16.250 1.4067 0.06454 0.05764 -0.0258 0.1331 1.0000
16.500 1.4136 0.06668 0.05993 -0.0259 0.1305 1.0000
16.750 1.4197 0.06892 0.06229 -0.0260 0.1277 1.0000
17.000 1.4239 0.07141 0.06489 -0.0262 0.1249 1.0000
17.250 1.4267 0.07410 0.06763 -0.0266 0.1222 1.0000
17.500 1.4285 0.07689 0.07044 -0.0269 0.1196 1.0000
17.750 1.4324 0.07960 0.07332 -0.0274 0.1169 1.0000
18.000 1.4342 0.08260 0.07646 -0.0281 0.1136 1.0000
18.250 1.4337 0.08591 0.07986 -0.0289 0.1104 1.0000
18.500 1.4302 0.08966 0.08362 -0.0299 0.1072 1.0000
18.750 1.4304 0.09306 0.08721 -0.0309 0.1036 1.0000
19.000 1.4275 0.09691 0.09118 -0.0322 0.0998 1.0000
19.250 1.4215 0.10124 0.09555 -0.0337 0.0962 1.0000
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