HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.29 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1585-il-1000000.txt Download as CSV file: xf-hq1585-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7257 0.04437 0.04262 -0.0455 1.0000 0.0064
-9.500 -0.7322 0.03976 0.03778 -0.0462 1.0000 0.0064
-9.250 -0.7634 0.02942 0.02665 -0.0463 1.0000 0.0064
-9.000 -0.7642 0.02363 0.02023 -0.0452 1.0000 0.0066
-8.750 -0.7506 0.02077 0.01701 -0.0443 1.0000 0.0068
-8.500 -0.7310 0.01940 0.01546 -0.0435 1.0000 0.0070
-8.250 -0.7087 0.01881 0.01481 -0.0429 1.0000 0.0073
-8.000 -0.6883 0.01765 0.01349 -0.0420 1.0000 0.0075
-7.750 -0.6669 0.01689 0.01263 -0.0412 1.0000 0.0079
-7.500 -0.6460 0.01627 0.01192 -0.0401 1.0000 0.0084
-7.250 -0.6140 0.01559 0.01113 -0.0414 0.9974 0.0090
-7.000 -0.5794 0.01527 0.01072 -0.0430 0.9934 0.0094
-6.750 -0.5502 0.01281 0.00800 -0.0442 0.9874 0.0105
-6.500 -0.5152 0.01238 0.00754 -0.0460 0.9830 0.0113
-6.250 -0.4822 0.01190 0.00701 -0.0473 0.9753 0.0123
-6.000 -0.4482 0.01144 0.00648 -0.0487 0.9674 0.0132
-5.750 -0.4161 0.01133 0.00631 -0.0496 0.9561 0.0138
-5.500 -0.3911 0.01005 0.00489 -0.0494 0.9413 0.0159
-5.250 -0.3648 0.00980 0.00458 -0.0491 0.9277 0.0172
-5.000 -0.3389 0.00950 0.00421 -0.0486 0.9152 0.0184
-4.750 -0.3125 0.00926 0.00390 -0.0483 0.9042 0.0194
-4.500 -0.2862 0.00896 0.00351 -0.0480 0.8944 0.0204
-4.250 -0.2603 0.00841 0.00285 -0.0475 0.8850 0.0230
-4.000 -0.2332 0.00817 0.00256 -0.0474 0.8765 0.0252
-3.750 -0.2061 0.00800 0.00234 -0.0472 0.8690 0.0275
-3.500 -0.1787 0.00774 0.00203 -0.0470 0.8613 0.0321
-3.250 -0.1516 0.00750 0.00180 -0.0469 0.8547 0.0451
-3.000 -0.1243 0.00723 0.00160 -0.0468 0.8477 0.0709
-2.750 -0.0981 0.00675 0.00140 -0.0467 0.8407 0.1549
-2.500 -0.0715 0.00634 0.00124 -0.0466 0.8325 0.2367
-2.250 -0.0449 0.00602 0.00113 -0.0465 0.8243 0.3129
-2.000 -0.0183 0.00566 0.00102 -0.0464 0.8162 0.4010
-1.750 0.0084 0.00532 0.00096 -0.0463 0.8088 0.4950
-1.500 0.0347 0.00504 0.00093 -0.0461 0.8007 0.5897
-1.250 0.0621 0.00493 0.00092 -0.0459 0.7922 0.6308
-1.000 0.0894 0.00488 0.00091 -0.0457 0.7840 0.6629
-0.750 0.1172 0.00484 0.00091 -0.0455 0.7757 0.6883
-0.500 0.1450 0.00483 0.00091 -0.0454 0.7689 0.7074
-0.250 0.1731 0.00481 0.00092 -0.0453 0.7619 0.7253
0.000 0.2011 0.00482 0.00092 -0.0453 0.7546 0.7368
0.250 0.2291 0.00482 0.00092 -0.0452 0.7456 0.7473
0.750 0.2851 0.00484 0.00094 -0.0450 0.7276 0.7677
1.000 0.3128 0.00484 0.00096 -0.0449 0.7155 0.7793
1.250 0.3402 0.00487 0.00096 -0.0447 0.6952 0.7896
1.500 0.3669 0.00497 0.00096 -0.0443 0.6613 0.7996
1.750 0.3932 0.00508 0.00099 -0.0439 0.6278 0.8099
2.000 0.4198 0.00519 0.00104 -0.0436 0.5955 0.8207
2.250 0.4461 0.00533 0.00111 -0.0433 0.5597 0.8320
2.500 0.4712 0.00561 0.00120 -0.0428 0.4963 0.8442
2.750 0.4952 0.00601 0.00136 -0.0421 0.4197 0.8590
3.000 0.5191 0.00634 0.00152 -0.0414 0.3551 0.8814
3.250 0.5421 0.00653 0.00167 -0.0404 0.3111 0.9263
3.500 0.5791 0.00679 0.00183 -0.0426 0.2677 1.0000
3.750 0.6052 0.00714 0.00200 -0.0424 0.2272 1.0000
4.000 0.6311 0.00749 0.00219 -0.0422 0.1924 1.0000
4.250 0.6566 0.00792 0.00242 -0.0420 0.1448 1.0000
4.500 0.6804 0.00859 0.00277 -0.0415 0.0820 1.0000
4.750 0.7051 0.00914 0.00312 -0.0411 0.0452 1.0000
5.000 0.7312 0.00947 0.00341 -0.0409 0.0391 1.0000
5.250 0.7576 0.00976 0.00374 -0.0406 0.0359 1.0000
5.500 0.7842 0.00999 0.00399 -0.0405 0.0346 1.0000
5.750 0.8105 0.01024 0.00426 -0.0403 0.0323 1.0000
6.000 0.8364 0.01056 0.00457 -0.0400 0.0294 1.0000
6.250 0.8614 0.01103 0.00511 -0.0396 0.0263 1.0000
6.500 0.8883 0.01115 0.00523 -0.0395 0.0253 1.0000
6.750 0.9153 0.01127 0.00534 -0.0395 0.0222 1.0000
7.000 0.9406 0.01163 0.00559 -0.0392 0.0137 1.0000
7.250 0.9650 0.01215 0.00608 -0.0387 0.0099 1.0000
7.500 0.9892 0.01272 0.00672 -0.0381 0.0083 1.0000
7.750 1.0135 0.01324 0.00729 -0.0376 0.0076 1.0000
8.000 1.0373 0.01379 0.00791 -0.0371 0.0071 1.0000
8.250 1.0605 0.01444 0.00863 -0.0364 0.0067 1.0000
8.500 1.0828 0.01518 0.00945 -0.0356 0.0063 1.0000
8.750 1.1030 0.01621 0.01060 -0.0346 0.0060 1.0000
9.000 1.1193 0.01777 0.01235 -0.0330 0.0057 1.0000
9.250 1.1412 0.01846 0.01313 -0.0322 0.0055 1.0000
9.500 1.1618 0.01931 0.01409 -0.0313 0.0054 1.0000
9.750 1.1811 0.02029 0.01519 -0.0303 0.0052 1.0000
10.000 1.1994 0.02138 0.01641 -0.0291 0.0050 1.0000
10.250 1.2158 0.02266 0.01783 -0.0277 0.0048 1.0000
10.500 1.2306 0.02408 0.01941 -0.0262 0.0047 1.0000
10.750 1.2435 0.02561 0.02110 -0.0245 0.0046 1.0000
11.000 1.2533 0.02740 0.02309 -0.0225 0.0045 1.0000
11.250 1.2598 0.02933 0.02522 -0.0202 0.0044 1.0000
11.500 1.2635 0.03096 0.02702 -0.0175 0.0044 1.0000
11.750 1.2607 0.03279 0.02903 -0.0141 0.0043 1.0000
12.000 1.2604 0.03438 0.03074 -0.0116 0.0042 1.0000
12.250 1.2545 0.03668 0.03320 -0.0093 0.0042 1.0000
12.500 1.2440 0.03971 0.03644 -0.0074 0.0042 1.0000
12.750 1.2346 0.04287 0.03977 -0.0065 0.0041 1.0000
13.000 1.2234 0.04656 0.04363 -0.0064 0.0041 1.0000
13.250 1.1986 0.05258 0.04990 -0.0076 0.0042 1.0000
13.500 1.1928 0.05646 0.05388 -0.0093 0.0041 1.0000
13.750 1.1860 0.06096 0.05848 -0.0117 0.0041 1.0000
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Polar data table (+)
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