HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/9 AIRFOIL (hq109-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.81 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq109-il-1000000.txt Download as CSV file: xf-hq109-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/9 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4899 0.15053 0.14902 0.0151 1.0000 0.0071
-13.500 -0.4892 0.14788 0.14636 0.0133 1.0000 0.0078
-8.250 -0.7299 0.02545 0.02207 -0.0341 1.0000 0.0059
-7.750 -0.7016 0.02033 0.01630 -0.0310 1.0000 0.0059
-7.500 -0.6831 0.01879 0.01454 -0.0296 1.0000 0.0057
-7.250 -0.6655 0.01707 0.01261 -0.0280 1.0000 0.0057
-7.000 -0.6473 0.01575 0.01111 -0.0264 1.0000 0.0057
-6.750 -0.6265 0.01389 0.00904 -0.0255 0.9991 0.0058
-6.500 -0.5943 0.01244 0.00742 -0.0269 0.9958 0.0063
-6.250 -0.5609 0.01178 0.00670 -0.0284 0.9923 0.0071
-6.000 -0.5279 0.01117 0.00602 -0.0298 0.9880 0.0078
-5.750 -0.4935 0.01056 0.00534 -0.0314 0.9844 0.0084
-5.500 -0.4599 0.01011 0.00483 -0.0327 0.9792 0.0089
-5.250 -0.4281 0.00925 0.00382 -0.0337 0.9715 0.0105
-5.000 -0.3970 0.00887 0.00342 -0.0345 0.9619 0.0132
-4.750 -0.3681 0.00844 0.00294 -0.0347 0.9498 0.0184
-4.500 -0.3413 0.00812 0.00264 -0.0345 0.9356 0.0318
-4.250 -0.3151 0.00790 0.00242 -0.0341 0.9215 0.0427
-4.000 -0.2890 0.00770 0.00222 -0.0337 0.9085 0.0547
-3.500 -0.2370 0.00724 0.00182 -0.0330 0.8845 0.1014
-3.250 -0.2118 0.00681 0.00163 -0.0327 0.8728 0.1719
-3.000 -0.1858 0.00650 0.00147 -0.0324 0.8616 0.2267
-2.750 -0.1601 0.00609 0.00129 -0.0322 0.8511 0.3063
-2.500 -0.1350 0.00560 0.00113 -0.0319 0.8415 0.4187
-2.250 -0.1090 0.00528 0.00104 -0.0316 0.8324 0.5006
-2.000 -0.0820 0.00512 0.00099 -0.0315 0.8239 0.5498
-1.750 -0.0548 0.00503 0.00095 -0.0313 0.8147 0.5844
-1.500 -0.0277 0.00495 0.00091 -0.0310 0.8037 0.6195
-1.250 -0.0003 0.00489 0.00088 -0.0309 0.7926 0.6444
-1.000 0.0272 0.00486 0.00087 -0.0307 0.7825 0.6666
-0.750 0.0546 0.00484 0.00086 -0.0305 0.7722 0.6880
-0.500 0.0821 0.00484 0.00084 -0.0304 0.7605 0.7037
-0.250 0.1098 0.00483 0.00083 -0.0302 0.7488 0.7183
0.000 0.1375 0.00483 0.00084 -0.0301 0.7383 0.7317
0.250 0.1652 0.00483 0.00084 -0.0300 0.7270 0.7436
0.500 0.1928 0.00484 0.00085 -0.0299 0.7154 0.7555
0.750 0.2204 0.00486 0.00087 -0.0298 0.7033 0.7671
1.000 0.2479 0.00488 0.00089 -0.0296 0.6906 0.7798
1.250 0.2753 0.00490 0.00091 -0.0295 0.6766 0.7926
1.500 0.3027 0.00494 0.00095 -0.0293 0.6598 0.8042
1.750 0.3299 0.00499 0.00098 -0.0291 0.6403 0.8154
2.000 0.3569 0.00505 0.00102 -0.0289 0.6197 0.8270
2.250 0.3835 0.00513 0.00107 -0.0286 0.5923 0.8398
2.500 0.4092 0.00528 0.00114 -0.0281 0.5486 0.8539
2.750 0.4348 0.00544 0.00123 -0.0276 0.5093 0.8702
3.000 0.4595 0.00562 0.00133 -0.0270 0.4652 0.8911
3.250 0.4829 0.00586 0.00147 -0.0260 0.4089 0.9219
3.500 0.5133 0.00623 0.00166 -0.0268 0.3376 0.9653
3.750 0.5519 0.00668 0.00187 -0.0295 0.2773 0.9947
4.000 0.5795 0.00700 0.00205 -0.0297 0.2431 1.0000
4.250 0.6047 0.00732 0.00223 -0.0294 0.2099 1.0000
4.500 0.6302 0.00761 0.00242 -0.0291 0.1814 1.0000
4.750 0.6555 0.00795 0.00264 -0.0287 0.1481 1.0000
5.000 0.6798 0.00842 0.00291 -0.0283 0.1078 1.0000
5.250 0.7043 0.00889 0.00322 -0.0279 0.0762 1.0000
5.500 0.7295 0.00925 0.00350 -0.0275 0.0582 1.0000
5.750 0.7548 0.00961 0.00379 -0.0272 0.0441 1.0000
6.000 0.7798 0.01001 0.00413 -0.0268 0.0308 1.0000
6.250 0.8047 0.01042 0.00449 -0.0264 0.0208 1.0000
6.500 0.8287 0.01099 0.00502 -0.0258 0.0114 1.0000
6.750 0.8534 0.01144 0.00548 -0.0253 0.0085 1.0000
7.000 0.8767 0.01215 0.00628 -0.0246 0.0068 1.0000
7.250 0.9012 0.01261 0.00680 -0.0241 0.0063 1.0000
7.500 0.9252 0.01314 0.00740 -0.0235 0.0056 1.0000
7.750 0.9486 0.01374 0.00806 -0.0229 0.0050 1.0000
8.000 0.9694 0.01473 0.00916 -0.0218 0.0046 1.0000
8.250 0.9889 0.01589 0.01046 -0.0206 0.0044 1.0000
8.500 1.0051 0.01755 0.01232 -0.0189 0.0043 1.0000
8.750 1.0226 0.01905 0.01398 -0.0175 0.0042 1.0000
9.000 1.0393 0.02071 0.01581 -0.0160 0.0042 1.0000
9.250 1.0547 0.02260 0.01790 -0.0144 0.0042 1.0000
9.500 1.0666 0.02503 0.02058 -0.0126 0.0042 1.0000
9.750 1.0781 0.02719 0.02299 -0.0108 0.0041 1.0000
10.000 1.0951 0.02807 0.02403 -0.0096 0.0040 1.0000
10.250 1.1050 0.02995 0.02611 -0.0078 0.0040 1.0000
10.500 1.1076 0.03249 0.02890 -0.0053 0.0040 1.0000
10.750 1.1005 0.03541 0.03210 -0.0018 0.0040 1.0000
11.000 1.0811 0.03862 0.03555 0.0026 0.0040 1.0000
11.250 1.0725 0.04095 0.03804 0.0049 0.0040 1.0000
11.500 1.0563 0.04443 0.04172 0.0064 0.0040 1.0000
11.750 1.0312 0.04967 0.04713 0.0064 0.0042 1.0000
12.000 1.0140 0.05449 0.05211 0.0050 0.0042 1.0000
12.250 1.0124 0.05770 0.05541 0.0034 0.0042 1.0000
12.500 0.9878 0.06528 0.06317 -0.0013 0.0042 1.0000
12.750 0.9729 0.07241 0.07043 -0.0064 0.0042 1.0000
13.000 0.9632 0.07947 0.07759 -0.0115 0.0042 1.0000
13.250 0.9505 0.08811 0.08634 -0.0175 0.0043 1.0000
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Polar data table (+)
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