HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 200,000 Max Cl/Cd: 41.37 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq010-il-200000-n5.txt Download as CSV file: xf-hq010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8067 0.10179 0.09837 0.0055 1.0000 0.0085
-13.000 -0.8454 0.08703 0.08358 -0.0030 1.0000 0.0077
-12.750 -0.8795 0.07371 0.07010 -0.0124 1.0000 0.0072
-12.500 -0.9086 0.06384 0.06002 -0.0196 1.0000 0.0069
-12.250 -0.9328 0.05660 0.05255 -0.0241 1.0000 0.0068
-12.000 -0.9507 0.05131 0.04704 -0.0264 1.0000 0.0069
-11.750 -0.9665 0.04691 0.04241 -0.0273 1.0000 0.0071
-11.500 -0.9804 0.04314 0.03838 -0.0270 1.0000 0.0070
-11.250 -0.9903 0.04009 0.03507 -0.0255 1.0000 0.0071
-11.000 -0.9967 0.03750 0.03221 -0.0232 1.0000 0.0076
-10.750 -0.9990 0.03502 0.02944 -0.0207 1.0000 0.0079
-10.500 -0.9935 0.03274 0.02681 -0.0189 1.0000 0.0086
-10.250 -0.9839 0.03116 0.02510 -0.0175 1.0000 0.0094
-10.000 -0.9658 0.03088 0.02480 -0.0169 1.0000 0.0107
-9.750 -0.9504 0.02965 0.02335 -0.0157 1.0000 0.0124
-9.500 -0.9335 0.02826 0.02160 -0.0146 1.0000 0.0138
-9.250 -0.9194 0.02662 0.01987 -0.0134 1.0000 0.0154
-9.000 -0.9001 0.02583 0.01897 -0.0127 1.0000 0.0170
-8.750 -0.8789 0.02530 0.01829 -0.0121 1.0000 0.0195
-8.500 -0.8565 0.02489 0.01766 -0.0115 1.0000 0.0212
-8.250 -0.8390 0.02320 0.01592 -0.0105 1.0000 0.0235
-8.000 -0.8176 0.02247 0.01511 -0.0099 1.0000 0.0255
-7.750 -0.7959 0.02156 0.01408 -0.0091 1.0000 0.0273
-7.500 -0.7746 0.02051 0.01286 -0.0082 1.0000 0.0286
-7.250 -0.7531 0.01957 0.01179 -0.0073 1.0000 0.0299
-7.000 -0.7311 0.01877 0.01087 -0.0065 1.0000 0.0309
-6.750 -0.7118 0.01764 0.00972 -0.0054 1.0000 0.0332
-6.500 -0.6903 0.01690 0.00895 -0.0045 1.0000 0.0358
-6.250 -0.6679 0.01632 0.00830 -0.0038 1.0000 0.0396
-6.000 -0.6458 0.01572 0.00764 -0.0029 1.0000 0.0441
-5.750 -0.6241 0.01511 0.00700 -0.0020 1.0000 0.0503
-5.500 -0.6022 0.01457 0.00645 -0.0011 1.0000 0.0578
-5.250 -0.5807 0.01408 0.00597 -0.0002 1.0000 0.0690
-5.000 -0.5605 0.01356 0.00553 0.0009 1.0000 0.0864
-4.750 -0.5326 0.01293 0.00505 0.0003 0.9923 0.1170
-4.500 -0.4998 0.01220 0.00465 -0.0015 0.9800 0.1836
-4.250 -0.4663 0.01167 0.00427 -0.0032 0.9686 0.2349
-4.000 -0.4341 0.01111 0.00392 -0.0046 0.9566 0.2892
-3.750 -0.4042 0.01047 0.00364 -0.0055 0.9438 0.3710
-3.500 -0.3749 0.01000 0.00343 -0.0061 0.9310 0.4476
-3.250 -0.3471 0.00964 0.00331 -0.0061 0.9183 0.5153
-3.000 -0.3197 0.00944 0.00327 -0.0059 0.9060 0.5728
-2.750 -0.2925 0.00934 0.00326 -0.0055 0.8946 0.6182
-2.500 -0.2655 0.00930 0.00323 -0.0050 0.8836 0.6489
-2.250 -0.2387 0.00927 0.00315 -0.0045 0.8715 0.6654
-2.000 -0.2122 0.00925 0.00307 -0.0040 0.8587 0.6785
-1.750 -0.1858 0.00924 0.00300 -0.0034 0.8463 0.6913
-1.500 -0.1592 0.00923 0.00295 -0.0029 0.8358 0.7046
-1.250 -0.1326 0.00923 0.00291 -0.0025 0.8264 0.7177
-1.000 -0.1060 0.00922 0.00288 -0.0020 0.8165 0.7293
-0.750 -0.0796 0.00921 0.00288 -0.0015 0.8064 0.7419
-0.500 -0.0532 0.00921 0.00288 -0.0009 0.7963 0.7549
-0.250 -0.0267 0.00921 0.00286 -0.0004 0.7864 0.7656
0.000 0.0000 0.00921 0.00286 0.0000 0.7756 0.7756
0.250 0.0268 0.00921 0.00286 0.0004 0.7656 0.7864
0.500 0.0532 0.00921 0.00288 0.0009 0.7548 0.7964
0.750 0.0796 0.00921 0.00288 0.0015 0.7419 0.8064
1.000 0.1061 0.00922 0.00288 0.0020 0.7293 0.8164
1.250 0.1326 0.00923 0.00291 0.0025 0.7177 0.8265
1.500 0.1592 0.00923 0.00295 0.0029 0.7046 0.8358
1.750 0.1858 0.00924 0.00300 0.0034 0.6913 0.8463
2.000 0.2122 0.00925 0.00307 0.0040 0.6785 0.8587
2.250 0.2387 0.00927 0.00315 0.0045 0.6654 0.8715
2.500 0.2655 0.00930 0.00323 0.0050 0.6488 0.8836
2.750 0.2925 0.00934 0.00326 0.0055 0.6180 0.8946
3.000 0.3197 0.00944 0.00327 0.0059 0.5729 0.9060
3.250 0.3471 0.00964 0.00331 0.0061 0.5150 0.9182
3.500 0.3750 0.01000 0.00343 0.0061 0.4481 0.9310
3.750 0.4042 0.01047 0.00364 0.0055 0.3712 0.9438
4.000 0.4341 0.01112 0.00392 0.0046 0.2889 0.9566
4.250 0.4663 0.01167 0.00427 0.0032 0.2347 0.9686
4.500 0.4998 0.01220 0.00465 0.0015 0.1840 0.9801
4.750 0.5326 0.01293 0.00505 -0.0003 0.1168 0.9923
5.000 0.5605 0.01355 0.00553 -0.0009 0.0864 1.0000
5.250 0.5807 0.01408 0.00597 0.0002 0.0689 1.0000
5.500 0.6022 0.01457 0.00645 0.0011 0.0579 1.0000
5.750 0.6241 0.01511 0.00700 0.0020 0.0503 1.0000
6.000 0.6457 0.01573 0.00765 0.0029 0.0438 1.0000
6.250 0.6679 0.01632 0.00830 0.0038 0.0395 1.0000
6.500 0.6903 0.01690 0.00894 0.0045 0.0357 1.0000
6.750 0.7119 0.01764 0.00972 0.0054 0.0332 1.0000
7.000 0.7311 0.01877 0.01087 0.0065 0.0309 1.0000
7.250 0.7531 0.01957 0.01179 0.0073 0.0298 1.0000
7.500 0.7746 0.02052 0.01287 0.0082 0.0286 1.0000
7.750 0.7959 0.02157 0.01409 0.0091 0.0273 1.0000
8.000 0.8175 0.02249 0.01513 0.0099 0.0255 1.0000
8.250 0.8389 0.02323 0.01595 0.0105 0.0236 1.0000
8.500 0.8566 0.02481 0.01759 0.0114 0.0212 1.0000
8.750 0.8791 0.02522 0.01821 0.0120 0.0194 1.0000
9.000 0.9001 0.02582 0.01896 0.0127 0.0170 1.0000
9.250 0.9194 0.02661 0.01986 0.0134 0.0154 1.0000
9.500 0.9333 0.02829 0.02163 0.0146 0.0138 1.0000
9.750 0.9502 0.02970 0.02341 0.0158 0.0124 1.0000
10.000 0.9656 0.03093 0.02485 0.0169 0.0107 1.0000
10.250 0.9831 0.03135 0.02531 0.0176 0.0095 1.0000
10.500 0.9933 0.03276 0.02683 0.0189 0.0086 1.0000
10.750 0.9993 0.03499 0.02939 0.0207 0.0080 1.0000
11.000 0.9968 0.03751 0.03222 0.0232 0.0076 1.0000
11.250 0.9901 0.04015 0.03513 0.0255 0.0073 1.0000
11.500 0.9805 0.04316 0.03840 0.0269 0.0070 1.0000
11.750 0.9678 0.04680 0.04228 0.0273 0.0069 1.0000
12.000 0.9530 0.05105 0.04677 0.0264 0.0067 1.0000
12.250 0.9329 0.05665 0.05261 0.0240 0.0068 1.0000
12.500 0.9098 0.06372 0.05990 0.0196 0.0069 1.0000
12.750 0.8784 0.07408 0.07048 0.0120 0.0073 1.0000
13.000 0.8388 0.08916 0.08574 0.0015 0.0076 1.0000
13.250 0.7890 0.10678 0.10335 -0.0080 0.0091 1.0000
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