HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.68 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2090sm-il-1000000.txt Download as CSV file: xf-hq2090sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3898 0.10544 0.10388 -0.0201 1.0000 0.0095
-10.750 -0.3900 0.10055 0.09900 -0.0218 1.0000 0.0095
-7.750 -0.5874 0.02071 0.01711 -0.0564 0.9915 0.0067
-7.500 -0.5589 0.01789 0.01389 -0.0579 0.9882 0.0067
-7.250 -0.5279 0.01604 0.01179 -0.0595 0.9858 0.0069
-7.000 -0.4948 0.01499 0.01060 -0.0612 0.9840 0.0073
-6.750 -0.4638 0.01377 0.00921 -0.0623 0.9806 0.0075
-6.500 -0.4346 0.01255 0.00782 -0.0628 0.9754 0.0077
-6.250 -0.4033 0.01166 0.00681 -0.0638 0.9711 0.0081
-6.000 -0.3755 0.01095 0.00600 -0.0639 0.9643 0.0087
-5.750 -0.3476 0.01044 0.00539 -0.0639 0.9572 0.0093
-5.500 -0.3227 0.00975 0.00458 -0.0633 0.9482 0.0100
-5.250 -0.2972 0.00917 0.00392 -0.0628 0.9400 0.0113
-5.000 -0.2713 0.00888 0.00358 -0.0624 0.9306 0.0126
-4.750 -0.2449 0.00864 0.00330 -0.0620 0.9216 0.0142
-4.500 -0.2189 0.00828 0.00290 -0.0616 0.9127 0.0192
-4.250 -0.1924 0.00798 0.00257 -0.0613 0.9028 0.0252
-4.000 -0.1654 0.00786 0.00242 -0.0611 0.8936 0.0289
-3.750 -0.1387 0.00761 0.00213 -0.0608 0.8847 0.0361
-3.500 -0.1114 0.00747 0.00194 -0.0606 0.8753 0.0419
-3.250 -0.0844 0.00728 0.00176 -0.0605 0.8659 0.0541
-3.000 -0.0575 0.00706 0.00159 -0.0603 0.8559 0.0784
-2.750 -0.0306 0.00681 0.00143 -0.0601 0.8458 0.1180
-2.500 -0.0038 0.00645 0.00128 -0.0601 0.8371 0.1893
-2.250 0.0219 0.00584 0.00110 -0.0601 0.8292 0.3330
-2.000 0.0482 0.00536 0.00101 -0.0600 0.8210 0.4632
-1.750 0.0753 0.00515 0.00096 -0.0599 0.8133 0.5310
-1.500 0.1024 0.00500 0.00093 -0.0598 0.8039 0.5864
-1.250 0.1298 0.00493 0.00092 -0.0596 0.7939 0.6229
-1.000 0.1573 0.00491 0.00091 -0.0594 0.7838 0.6501
-0.750 0.1850 0.00491 0.00089 -0.0593 0.7737 0.6681
-0.500 0.2130 0.00490 0.00089 -0.0592 0.7647 0.6876
-0.250 0.2406 0.00490 0.00090 -0.0591 0.7563 0.7056
0.000 0.2681 0.00490 0.00093 -0.0589 0.7468 0.7277
0.250 0.2958 0.00491 0.00094 -0.0588 0.7360 0.7428
0.500 0.3234 0.00492 0.00095 -0.0586 0.7245 0.7517
0.750 0.3512 0.00495 0.00095 -0.0585 0.7134 0.7602
1.250 0.4064 0.00501 0.00100 -0.0583 0.6892 0.7779
1.500 0.4341 0.00504 0.00102 -0.0582 0.6759 0.7874
1.750 0.4614 0.00509 0.00106 -0.0581 0.6602 0.7977
2.000 0.4886 0.00513 0.00110 -0.0579 0.6429 0.8088
2.250 0.5154 0.00519 0.00116 -0.0576 0.6209 0.8216
2.500 0.5416 0.00528 0.00122 -0.0572 0.5929 0.8371
3.000 0.5897 0.00568 0.00143 -0.0557 0.4974 0.8876
3.250 0.6134 0.00586 0.00157 -0.0548 0.4470 0.9487
3.500 0.6473 0.00624 0.00173 -0.0564 0.3904 1.0000
3.750 0.6724 0.00664 0.00191 -0.0561 0.3385 1.0000
4.000 0.6976 0.00703 0.00212 -0.0558 0.2934 1.0000
4.250 0.7235 0.00734 0.00231 -0.0555 0.2625 1.0000
4.500 0.7493 0.00765 0.00251 -0.0553 0.2355 1.0000
4.750 0.7750 0.00798 0.00272 -0.0550 0.2052 1.0000
5.000 0.8002 0.00835 0.00296 -0.0547 0.1738 1.0000
5.250 0.8249 0.00880 0.00324 -0.0543 0.1392 1.0000
5.500 0.8488 0.00933 0.00357 -0.0539 0.0994 1.0000
5.750 0.8729 0.00984 0.00393 -0.0534 0.0698 1.0000
6.000 0.8974 0.01029 0.00428 -0.0530 0.0527 1.0000
6.250 0.9225 0.01065 0.00462 -0.0526 0.0428 1.0000
6.500 0.9479 0.01098 0.00494 -0.0523 0.0362 1.0000
6.750 0.9726 0.01138 0.00531 -0.0519 0.0291 1.0000
7.000 0.9972 0.01178 0.00567 -0.0515 0.0222 1.0000
7.250 1.0207 0.01232 0.00617 -0.0509 0.0138 1.0000
7.500 1.0443 0.01286 0.00670 -0.0502 0.0105 1.0000
7.750 1.0675 0.01345 0.00737 -0.0495 0.0090 1.0000
8.000 1.0909 0.01397 0.00795 -0.0489 0.0082 1.0000
8.250 1.1137 0.01454 0.00857 -0.0482 0.0075 1.0000
8.500 1.1350 0.01529 0.00939 -0.0472 0.0068 1.0000
8.750 1.1510 0.01668 0.01095 -0.0455 0.0062 1.0000
9.000 1.1730 0.01727 0.01161 -0.0447 0.0060 1.0000
9.250 1.1931 0.01806 0.01251 -0.0436 0.0058 1.0000
9.500 1.2130 0.01882 0.01335 -0.0426 0.0054 1.0000
9.750 1.2322 0.01963 0.01424 -0.0414 0.0051 1.0000
10.000 1.2505 0.02048 0.01518 -0.0402 0.0048 1.0000
10.250 1.2675 0.02141 0.01620 -0.0389 0.0047 1.0000
10.500 1.2827 0.02247 0.01736 -0.0373 0.0045 1.0000
10.750 1.2956 0.02370 0.01870 -0.0354 0.0044 1.0000
11.000 1.3043 0.02522 0.02036 -0.0331 0.0042 1.0000
11.250 1.3079 0.02677 0.02205 -0.0299 0.0041 1.0000
11.500 1.3055 0.02874 0.02421 -0.0262 0.0040 1.0000
11.750 1.3021 0.03087 0.02654 -0.0229 0.0040 1.0000
12.000 1.2968 0.03328 0.02914 -0.0199 0.0040 1.0000
12.250 1.2824 0.03673 0.03285 -0.0169 0.0039 1.0000
12.500 1.2678 0.04040 0.03676 -0.0148 0.0039 1.0000
12.750 1.2605 0.04347 0.03999 -0.0137 0.0039 1.0000
13.000 1.2428 0.04802 0.04477 -0.0132 0.0038 1.0000
13.250 1.2343 0.05175 0.04865 -0.0136 0.0038 1.0000
13.500 1.2422 0.05349 0.05047 -0.0141 0.0037 1.0000
13.750 1.2235 0.05932 0.05649 -0.0160 0.0038 1.0000
14.000 1.2093 0.06504 0.06237 -0.0186 0.0038 1.0000
14.250 1.1904 0.07226 0.06977 -0.0226 0.0038 1.0000
14.500 1.1558 0.08341 0.08113 -0.0293 0.0038 1.0000
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Polar data table (+)
Polar graphs
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