HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 200,000 Max Cl/Cd: 73.86 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2090sm-il-200000.txt Download as CSV file: xf-hq2090sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ-2.0/9 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3785 0.09375 0.09040 -0.0257 1.0000 0.0434
-9.500 -0.4805 0.09672 0.09324 -0.0321 1.0000 0.0403
-9.250 -0.4727 0.09275 0.08927 -0.0291 1.0000 0.0416
-9.000 -0.4670 0.08965 0.08616 -0.0291 1.0000 0.0425
-8.750 -0.4634 0.08643 0.08297 -0.0297 1.0000 0.0436
-8.500 -0.4626 0.08291 0.07950 -0.0311 1.0000 0.0446
-8.250 -0.4646 0.07915 0.07578 -0.0330 1.0000 0.0454
-8.000 -0.4711 0.07511 0.07181 -0.0353 1.0000 0.0464
-7.750 -0.4797 0.07025 0.06701 -0.0400 1.0000 0.0467
-7.500 -0.4856 0.06545 0.06218 -0.0434 1.0000 0.0480
-7.250 -0.4898 0.06119 0.05784 -0.0452 1.0000 0.0492
-7.000 -0.4982 0.05866 0.05482 -0.0465 1.0000 0.0522
-6.750 -0.4988 0.05638 0.05228 -0.0448 1.0000 0.0524
-6.500 -0.5031 0.04920 0.04522 -0.0441 1.0000 0.0539
-6.250 -0.4976 0.04655 0.04259 -0.0423 1.0000 0.0551
-6.000 -0.4915 0.04419 0.04018 -0.0406 1.0000 0.0567
-5.750 -0.4837 0.04172 0.03756 -0.0391 1.0000 0.0590
-5.500 -0.4747 0.03909 0.03423 -0.0381 1.0000 0.0667
-5.250 -0.4484 0.02661 0.02044 -0.0365 0.9996 0.0299
-5.000 -0.4144 0.02467 0.01844 -0.0392 0.9960 0.0338
-4.750 -0.3786 0.02180 0.01505 -0.0407 0.9930 0.0344
-4.500 -0.3434 0.01956 0.01242 -0.0419 0.9893 0.0359
-4.250 -0.3062 0.01825 0.01079 -0.0435 0.9857 0.0394
-4.000 -0.2695 0.01667 0.00917 -0.0456 0.9829 0.0478
-3.750 -0.2373 0.01553 0.00799 -0.0466 0.9777 0.0572
-3.500 -0.2012 0.01467 0.00711 -0.0485 0.9732 0.0695
-3.250 -0.1622 0.01392 0.00639 -0.0510 0.9699 0.0876
-3.000 -0.1304 0.01319 0.00577 -0.0522 0.9637 0.1213
-2.750 -0.1003 0.01113 0.00530 -0.0541 0.9592 0.4676
-2.500 -0.0648 0.01077 0.00550 -0.0553 0.9558 0.6470
-2.250 -0.0364 0.01078 0.00553 -0.0551 0.9482 0.6993
-2.000 0.0007 0.01076 0.00553 -0.0565 0.9441 0.7401
-1.750 0.0348 0.01073 0.00550 -0.0574 0.9389 0.7708
-1.500 0.0653 0.01066 0.00545 -0.0574 0.9320 0.7976
-1.250 0.0992 0.01054 0.00537 -0.0577 0.9278 0.8302
-1.000 0.1199 0.01046 0.00536 -0.0554 0.9184 0.8607
-0.750 0.1518 0.01030 0.00519 -0.0555 0.9137 0.8818
-0.500 0.1763 0.01021 0.00509 -0.0545 0.9045 0.8985
-0.250 0.2093 0.01005 0.00490 -0.0550 0.8996 0.9142
0.000 0.2388 0.00996 0.00482 -0.0551 0.8908 0.9318
0.250 0.2786 0.00977 0.00460 -0.0570 0.8852 0.9475
0.500 0.3186 0.00959 0.00440 -0.0592 0.8743 0.9639
0.750 0.3610 0.00941 0.00419 -0.0620 0.8636 0.9802
1.000 0.4053 0.00926 0.00402 -0.0653 0.8550 0.9978
1.250 0.4262 0.00924 0.00395 -0.0642 0.8438 1.0000
1.500 0.4489 0.00926 0.00393 -0.0633 0.8314 1.0000
1.750 0.4738 0.00928 0.00390 -0.0626 0.8186 1.0000
2.000 0.4993 0.00929 0.00390 -0.0620 0.8052 1.0000
2.250 0.5252 0.00931 0.00389 -0.0613 0.7915 1.0000
2.500 0.5512 0.00934 0.00390 -0.0607 0.7773 1.0000
2.750 0.5773 0.00938 0.00392 -0.0601 0.7622 1.0000
3.000 0.6034 0.00941 0.00396 -0.0595 0.7460 1.0000
3.250 0.6293 0.00947 0.00401 -0.0588 0.7279 1.0000
3.500 0.6549 0.00952 0.00407 -0.0581 0.7064 1.0000
3.750 0.6802 0.00959 0.00412 -0.0573 0.6812 1.0000
4.000 0.7046 0.00969 0.00416 -0.0562 0.6464 1.0000
4.250 0.7283 0.00986 0.00422 -0.0551 0.6013 1.0000
4.500 0.7512 0.01017 0.00434 -0.0539 0.5480 1.0000
4.750 0.7727 0.01065 0.00456 -0.0526 0.4840 1.0000
5.000 0.7933 0.01129 0.00489 -0.0513 0.4209 1.0000
5.250 0.8143 0.01194 0.00533 -0.0503 0.3622 1.0000
5.500 0.8352 0.01265 0.00579 -0.0493 0.3076 1.0000
5.750 0.8566 0.01335 0.00631 -0.0484 0.2606 1.0000
6.000 0.8777 0.01409 0.00688 -0.0475 0.2124 1.0000
6.250 0.8968 0.01511 0.00757 -0.0464 0.1499 1.0000
6.500 0.9147 0.01636 0.00853 -0.0451 0.1042 1.0000
6.750 0.9342 0.01741 0.00948 -0.0439 0.0815 1.0000
7.000 0.9535 0.01847 0.01048 -0.0428 0.0661 1.0000
7.250 0.9725 0.01958 0.01159 -0.0416 0.0538 1.0000
7.500 0.9907 0.02091 0.01297 -0.0402 0.0437 1.0000
7.750 1.0077 0.02264 0.01475 -0.0385 0.0365 1.0000
8.000 1.0262 0.02394 0.01608 -0.0374 0.0307 1.0000
8.250 1.0454 0.02626 0.01855 -0.0361 0.0281 1.0000
8.500 1.0666 0.02816 0.02066 -0.0349 0.0262 1.0000
8.750 1.0870 0.03035 0.02309 -0.0338 0.0248 1.0000
9.000 1.1051 0.03220 0.02512 -0.0327 0.0232 1.0000
9.250 1.1207 0.03466 0.02770 -0.0316 0.0215 1.0000
9.500 1.1274 0.03981 0.03331 -0.0297 0.0207 1.0000
9.750 1.1349 0.04261 0.03651 -0.0275 0.0204 1.0000
10.000 1.1367 0.04613 0.04042 -0.0251 0.0204 1.0000
10.250 1.1326 0.05021 0.04486 -0.0225 0.0205 1.0000
10.500 1.1224 0.05432 0.04929 -0.0197 0.0205 1.0000
10.750 1.1128 0.05804 0.05324 -0.0170 0.0208 1.0000
11.000 1.1001 0.06091 0.05632 -0.0145 0.0209 1.0000
11.250 1.0898 0.06353 0.05914 -0.0129 0.0211 1.0000
11.500 1.0745 0.06709 0.06291 -0.0123 0.0213 1.0000
11.750 1.0554 0.07145 0.06753 -0.0130 0.0217 1.0000
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Polar data table (+)
Polar graphs
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