HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 500,000 Max Cl/Cd: 79.61 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq209-il-500000-n5.txt Download as CSV file: xf-hq209-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4774 0.08384 0.08161 -0.0284 1.0000 0.0043
-9.000 -0.4798 0.07944 0.07724 -0.0307 1.0000 0.0042
-8.750 -0.4876 0.07399 0.07184 -0.0338 1.0000 0.0041
-8.500 -0.4984 0.06848 0.06638 -0.0373 1.0000 0.0041
-8.250 -0.5140 0.06174 0.05966 -0.0443 1.0000 0.0041
-8.000 -0.5264 0.05500 0.05283 -0.0480 1.0000 0.0040
-7.750 -0.5291 0.04657 0.04417 -0.0527 0.9947 0.0040
-7.500 -0.5309 0.02630 0.02263 -0.0601 0.9795 0.0039
-7.250 -0.5064 0.02123 0.01683 -0.0618 0.9731 0.0042
-7.000 -0.4796 0.01886 0.01403 -0.0625 0.9658 0.0045
-6.750 -0.4497 0.01734 0.01221 -0.0635 0.9599 0.0047
-6.500 -0.4235 0.01536 0.00992 -0.0638 0.9516 0.0052
-6.250 -0.3945 0.01445 0.00887 -0.0644 0.9445 0.0056
-6.000 -0.3671 0.01386 0.00819 -0.0646 0.9355 0.0062
-5.750 -0.3396 0.01329 0.00752 -0.0646 0.9271 0.0069
-5.500 -0.3125 0.01274 0.00686 -0.0646 0.9187 0.0077
-5.250 -0.2864 0.01211 0.00606 -0.0642 0.9101 0.0081
-5.000 -0.2610 0.01127 0.00507 -0.0638 0.9023 0.0088
-4.750 -0.2351 0.01070 0.00439 -0.0635 0.8941 0.0098
-4.500 -0.2086 0.01035 0.00399 -0.0633 0.8869 0.0113
-4.250 -0.1819 0.01005 0.00360 -0.0630 0.8794 0.0128
-4.000 -0.1550 0.00971 0.00316 -0.0628 0.8725 0.0146
-3.750 -0.1282 0.00939 0.00281 -0.0625 0.8654 0.0219
-3.500 -0.1011 0.00916 0.00257 -0.0624 0.8588 0.0332
-3.250 -0.0740 0.00896 0.00236 -0.0623 0.8519 0.0439
-3.000 -0.0470 0.00872 0.00218 -0.0622 0.8452 0.0647
-2.750 -0.0202 0.00842 0.00199 -0.0621 0.8380 0.1021
-2.500 0.0067 0.00813 0.00181 -0.0620 0.8308 0.1493
-2.250 0.0331 0.00775 0.00164 -0.0619 0.8229 0.2276
-2.000 0.0592 0.00727 0.00148 -0.0619 0.8142 0.3335
-1.750 0.0852 0.00686 0.00137 -0.0617 0.8055 0.4433
-1.500 0.1118 0.00663 0.00131 -0.0615 0.7962 0.5146
-1.250 0.1382 0.00646 0.00129 -0.0612 0.7851 0.5791
-1.000 0.1649 0.00638 0.00127 -0.0608 0.7724 0.6206
-0.750 0.1915 0.00633 0.00127 -0.0604 0.7594 0.6573
-0.500 0.2185 0.00631 0.00125 -0.0601 0.7474 0.6825
-0.250 0.2454 0.00630 0.00125 -0.0598 0.7349 0.7040
0.000 0.2724 0.00632 0.00125 -0.0595 0.7213 0.7229
0.250 0.2996 0.00634 0.00125 -0.0593 0.7068 0.7337
0.500 0.3267 0.00638 0.00124 -0.0591 0.6908 0.7427
0.750 0.3540 0.00643 0.00126 -0.0589 0.6764 0.7524
1.000 0.3811 0.00648 0.00128 -0.0587 0.6627 0.7623
1.250 0.4081 0.00654 0.00132 -0.0584 0.6466 0.7722
1.500 0.4349 0.00661 0.00136 -0.0581 0.6298 0.7829
1.750 0.4616 0.00668 0.00141 -0.0579 0.6112 0.7942
2.000 0.4879 0.00678 0.00147 -0.0575 0.5886 0.8065
2.250 0.5138 0.00689 0.00156 -0.0571 0.5632 0.8196
2.500 0.5391 0.00704 0.00165 -0.0565 0.5327 0.8343
2.750 0.5638 0.00721 0.00176 -0.0559 0.4971 0.8510
3.000 0.5875 0.00741 0.00189 -0.0551 0.4574 0.8732
3.250 0.6106 0.00767 0.00205 -0.0541 0.4086 0.9114
3.500 0.6448 0.00822 0.00231 -0.0559 0.3271 1.0000
3.750 0.6686 0.00873 0.00256 -0.0554 0.2734 1.0000
4.000 0.6942 0.00904 0.00277 -0.0552 0.2503 1.0000
4.250 0.7203 0.00930 0.00298 -0.0550 0.2340 1.0000
4.500 0.7459 0.00960 0.00322 -0.0547 0.2134 1.0000
4.750 0.7710 0.00995 0.00347 -0.0544 0.1856 1.0000
5.000 0.7951 0.01043 0.00375 -0.0540 0.1451 1.0000
5.250 0.8176 0.01110 0.00415 -0.0533 0.0955 1.0000
5.500 0.8410 0.01167 0.00455 -0.0528 0.0646 1.0000
6.000 0.8890 0.01261 0.00535 -0.0519 0.0339 1.0000
6.250 0.9139 0.01297 0.00571 -0.0515 0.0272 1.0000
6.500 0.9382 0.01339 0.00611 -0.0510 0.0213 1.0000
6.750 0.9622 0.01385 0.00656 -0.0505 0.0152 1.0000
7.000 0.9850 0.01444 0.00712 -0.0498 0.0068 1.0000
7.250 1.0081 0.01499 0.00770 -0.0492 0.0048 1.0000
7.500 1.0308 0.01557 0.00835 -0.0484 0.0041 1.0000
7.750 1.0529 0.01622 0.00911 -0.0476 0.0034 1.0000
8.000 1.0747 0.01688 0.00988 -0.0468 0.0031 1.0000
8.250 1.0958 0.01764 0.01076 -0.0458 0.0029 1.0000
8.500 1.1159 0.01847 0.01171 -0.0448 0.0027 1.0000
8.750 1.1363 0.01924 0.01259 -0.0438 0.0026 1.0000
9.000 1.1554 0.02010 0.01357 -0.0426 0.0025 1.0000
9.250 1.1733 0.02108 0.01467 -0.0413 0.0024 1.0000
9.500 1.1902 0.02209 0.01581 -0.0399 0.0023 1.0000
9.750 1.2051 0.02327 0.01713 -0.0383 0.0022 1.0000
10.000 1.2185 0.02453 0.01858 -0.0364 0.0021 1.0000
10.250 1.2300 0.02587 0.02008 -0.0344 0.0020 1.0000
10.500 1.2392 0.02719 0.02156 -0.0321 0.0020 1.0000
10.750 1.2450 0.02860 0.02312 -0.0293 0.0020 1.0000
11.000 1.2479 0.03024 0.02494 -0.0265 0.0020 1.0000
11.250 1.2501 0.03198 0.02685 -0.0239 0.0019 1.0000
11.500 1.2498 0.03399 0.02905 -0.0214 0.0019 1.0000
11.750 1.2488 0.03615 0.03140 -0.0193 0.0019 1.0000
12.000 1.2451 0.03869 0.03413 -0.0176 0.0019 1.0000
12.250 1.2406 0.04146 0.03709 -0.0162 0.0019 1.0000
12.500 1.2337 0.04468 0.04051 -0.0154 0.0019 1.0000
12.750 1.2251 0.04833 0.04437 -0.0152 0.0019 1.0000
13.000 1.2142 0.05260 0.04883 -0.0157 0.0019 1.0000
13.250 1.2011 0.05755 0.05398 -0.0171 0.0019 1.0000
13.500 1.1882 0.06297 0.05959 -0.0193 0.0019 1.0000
13.750 1.1716 0.06958 0.06640 -0.0227 0.0019 1.0000
14.000 1.1551 0.07692 0.07391 -0.0270 0.0019 1.0000
14.250 1.1364 0.08542 0.08259 -0.0322 0.0019 1.0000
14.500 1.1178 0.09461 0.09194 -0.0378 0.0019 1.0000
14.750 1.0961 0.10503 0.10251 -0.0441 0.0019 1.0000
15.000 1.0745 0.11563 0.11324 -0.0502 0.0019 1.0000
15.250 1.0529 0.12654 0.12426 -0.0563 0.0020 1.0000
15.500 1.0319 0.13768 0.13549 -0.0624 0.0020 1.0000
15.750 1.0058 0.15114 0.14904 -0.0694 0.0021 1.0000
16.000 0.9758 0.16700 0.16496 -0.0773 0.0022 1.0000
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