CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Y AIRFOIL (clarky-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.8 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarky-il-1000000.txt Download as CSV file: xf-clarky-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Y 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3156 0.14464 0.14298 -0.0315 1.0000 0.0162
-14.500 -1.0248 0.03605 0.03333 -0.0892 1.0000 0.0164
-14.250 -1.0371 0.03284 0.02999 -0.0896 1.0000 0.0166
-14.000 -1.0347 0.03166 0.02877 -0.0877 1.0000 0.0169
-13.750 -1.0214 0.03117 0.02828 -0.0864 1.0000 0.0171
-13.500 -1.0070 0.03090 0.02801 -0.0848 1.0000 0.0174
-13.250 -0.9948 0.03059 0.02769 -0.0828 1.0000 0.0176
-13.000 -0.9847 0.03027 0.02735 -0.0804 1.0000 0.0179
-12.750 -0.9771 0.02987 0.02691 -0.0777 1.0000 0.0182
-12.500 -0.9635 0.02930 0.02628 -0.0762 0.9996 0.0186
-12.250 -0.9347 0.02845 0.02533 -0.0778 0.9981 0.0192
-12.000 -0.9045 0.02781 0.02458 -0.0793 0.9966 0.0196
-11.750 -0.8800 0.02584 0.02237 -0.0812 0.9947 0.0201
-11.500 -0.8522 0.02475 0.02122 -0.0827 0.9932 0.0206
-11.250 -0.8218 0.02455 0.02103 -0.0837 0.9910 0.0210
-11.000 -0.7899 0.02444 0.02093 -0.0850 0.9891 0.0214
-10.750 -0.7579 0.02416 0.02062 -0.0864 0.9873 0.0219
-10.500 -0.7261 0.02364 0.02003 -0.0879 0.9859 0.0225
-10.250 -0.6946 0.02280 0.01907 -0.0896 0.9846 0.0232
-10.000 -0.6628 0.02209 0.01823 -0.0911 0.9833 0.0237
-9.750 -0.6348 0.02188 0.01793 -0.0915 0.9791 0.0241
-9.500 -0.6138 0.01942 0.01521 -0.0919 0.9744 0.0249
-9.250 -0.5853 0.01872 0.01449 -0.0926 0.9712 0.0254
-9.000 -0.5602 0.01823 0.01395 -0.0924 0.9655 0.0259
-8.750 -0.5348 0.01779 0.01345 -0.0921 0.9596 0.0264
-8.500 -0.5089 0.01733 0.01294 -0.0920 0.9542 0.0270
-8.250 -0.4853 0.01678 0.01229 -0.0913 0.9467 0.0276
-8.000 -0.4604 0.01615 0.01154 -0.0908 0.9405 0.0280
-7.750 -0.4358 0.01569 0.01100 -0.0903 0.9326 0.0286
-7.500 -0.4099 0.01537 0.01058 -0.0899 0.9259 0.0290
-7.250 -0.3842 0.01500 0.01011 -0.0895 0.9180 0.0293
-7.000 -0.3599 0.01406 0.00901 -0.0889 0.9107 0.0297
-6.750 -0.3365 0.01283 0.00769 -0.0884 0.9026 0.0304
-6.500 -0.3112 0.01219 0.00697 -0.0879 0.8951 0.0308
-6.250 -0.2852 0.01169 0.00643 -0.0876 0.8870 0.0313
-5.750 -0.2325 0.01090 0.00553 -0.0870 0.8711 0.0322
-5.500 -0.2059 0.01057 0.00512 -0.0867 0.8633 0.0328
-5.250 -0.1791 0.01026 0.00476 -0.0864 0.8543 0.0334
-5.000 -0.1523 0.00999 0.00443 -0.0862 0.8450 0.0341
-4.750 -0.1255 0.00972 0.00409 -0.0859 0.8348 0.0346
-4.500 -0.0985 0.00947 0.00378 -0.0856 0.8253 0.0350
-4.250 -0.0714 0.00926 0.00350 -0.0854 0.8165 0.0354
-4.000 -0.0440 0.00908 0.00327 -0.0852 0.8067 0.0357
-3.750 -0.0175 0.00870 0.00281 -0.0849 0.7972 0.0369
-3.500 0.0096 0.00847 0.00252 -0.0846 0.7879 0.0381
-3.250 0.0371 0.00830 0.00232 -0.0845 0.7787 0.0394
-3.000 0.0645 0.00818 0.00214 -0.0843 0.7689 0.0407
-2.750 0.0922 0.00806 0.00199 -0.0841 0.7587 0.0422
-2.500 0.1198 0.00796 0.00184 -0.0840 0.7486 0.0440
-2.250 0.1471 0.00784 0.00170 -0.0838 0.7388 0.0488
-2.000 0.1747 0.00767 0.00160 -0.0837 0.7297 0.0659
-1.750 0.2020 0.00752 0.00151 -0.0835 0.7209 0.0930
-1.500 0.2293 0.00737 0.00143 -0.0834 0.7112 0.1210
-1.250 0.2564 0.00718 0.00137 -0.0833 0.7019 0.1672
-1.000 0.2833 0.00701 0.00133 -0.0831 0.6927 0.2229
-0.750 0.3107 0.00686 0.00131 -0.0830 0.6834 0.2696
-0.500 0.3380 0.00677 0.00130 -0.0829 0.6741 0.3090
-0.250 0.3651 0.00664 0.00128 -0.0828 0.6638 0.3575
0.000 0.3918 0.00645 0.00128 -0.0826 0.6533 0.4324
0.250 0.4171 0.00614 0.00130 -0.0822 0.6422 0.5591
0.500 0.4408 0.00578 0.00134 -0.0814 0.6307 0.7081
0.750 0.4632 0.00547 0.00141 -0.0800 0.6194 0.8388
1.000 0.4866 0.00538 0.00150 -0.0786 0.6079 0.9226
1.250 0.5201 0.00546 0.00157 -0.0796 0.5950 0.9665
1.500 0.5600 0.00558 0.00162 -0.0821 0.5805 0.9856
1.750 0.6022 0.00572 0.00167 -0.0853 0.5639 0.9946
2.000 0.6464 0.00585 0.00171 -0.0889 0.5456 1.0000
2.250 0.6708 0.00598 0.00176 -0.0882 0.5297 1.0000
2.500 0.6949 0.00612 0.00182 -0.0874 0.5128 1.0000
2.750 0.7187 0.00628 0.00189 -0.0866 0.4935 1.0000
3.000 0.7423 0.00647 0.00198 -0.0857 0.4720 1.0000
3.250 0.7650 0.00672 0.00209 -0.0847 0.4436 1.0000
3.500 0.7870 0.00702 0.00223 -0.0836 0.4086 1.0000
3.750 0.8091 0.00733 0.00238 -0.0825 0.3791 1.0000
4.000 0.8326 0.00757 0.00252 -0.0816 0.3604 1.0000
4.250 0.8567 0.00779 0.00267 -0.0809 0.3459 1.0000
4.500 0.8810 0.00801 0.00282 -0.0802 0.3335 1.0000
4.750 0.9060 0.00819 0.00296 -0.0797 0.3242 1.0000
5.000 0.9314 0.00836 0.00311 -0.0793 0.3174 1.0000
5.250 0.9570 0.00852 0.00325 -0.0788 0.3109 1.0000
5.500 0.9822 0.00872 0.00342 -0.0784 0.3038 1.0000
5.750 1.0081 0.00886 0.00357 -0.0780 0.2974 1.0000
6.000 1.0330 0.00909 0.00375 -0.0775 0.2894 1.0000
6.250 1.0590 0.00923 0.00390 -0.0772 0.2817 1.0000
6.500 1.0840 0.00945 0.00408 -0.0768 0.2718 1.0000
6.750 1.1090 0.00966 0.00426 -0.0763 0.2614 1.0000
7.000 1.1341 0.00988 0.00445 -0.0759 0.2500 1.0000
7.250 1.1584 0.01014 0.00466 -0.0754 0.2364 1.0000
7.500 1.1816 0.01048 0.00491 -0.0747 0.2176 1.0000
7.750 1.2028 0.01097 0.00525 -0.0737 0.1896 1.0000
8.250 1.2407 0.01224 0.00619 -0.0710 0.1327 1.0000
8.500 1.2606 0.01279 0.00663 -0.0699 0.1136 1.0000
8.750 1.2805 0.01333 0.00708 -0.0687 0.0988 1.0000
9.000 1.3008 0.01381 0.00752 -0.0676 0.0880 1.0000
9.250 1.3208 0.01430 0.00796 -0.0665 0.0790 1.0000
9.500 1.3401 0.01481 0.00841 -0.0653 0.0698 1.0000
9.750 1.3571 0.01539 0.00893 -0.0636 0.0573 1.0000
10.000 1.3618 0.01664 0.00992 -0.0602 0.0254 1.0000
10.250 1.3715 0.01761 0.01085 -0.0575 0.0168 1.0000
10.500 1.3856 0.01831 0.01159 -0.0555 0.0149 1.0000
10.750 1.4007 0.01897 0.01230 -0.0538 0.0139 1.0000
11.000 1.4136 0.01976 0.01313 -0.0519 0.0130 1.0000
11.250 1.4236 0.02077 0.01422 -0.0497 0.0121 1.0000
11.500 1.4375 0.02154 0.01504 -0.0481 0.0118 1.0000
11.750 1.4503 0.02239 0.01595 -0.0464 0.0113 1.0000
12.000 1.4619 0.02335 0.01697 -0.0447 0.0109 1.0000
12.250 1.4724 0.02441 0.01809 -0.0431 0.0105 1.0000
12.500 1.4810 0.02565 0.01939 -0.0413 0.0101 1.0000
12.750 1.4847 0.02733 0.02115 -0.0393 0.0097 1.0000
13.000 1.4888 0.02903 0.02295 -0.0375 0.0094 1.0000
13.250 1.4985 0.03033 0.02432 -0.0363 0.0092 1.0000
13.500 1.5063 0.03185 0.02591 -0.0352 0.0089 1.0000
13.750 1.5122 0.03356 0.02770 -0.0340 0.0087 1.0000
14.000 1.5169 0.03546 0.02968 -0.0329 0.0085 1.0000
14.250 1.5205 0.03753 0.03183 -0.0320 0.0083 1.0000
14.500 1.5231 0.03975 0.03412 -0.0312 0.0081 1.0000
14.750 1.5240 0.04222 0.03668 -0.0305 0.0079 1.0000
15.000 1.5231 0.04500 0.03955 -0.0299 0.0078 1.0000
15.250 1.5193 0.04819 0.04284 -0.0296 0.0076 1.0000
15.500 1.5118 0.05198 0.04673 -0.0295 0.0075 1.0000
15.750 1.5001 0.05647 0.05134 -0.0298 0.0074 1.0000
16.000 1.4855 0.06151 0.05651 -0.0304 0.0073 1.0000
16.250 1.4724 0.06656 0.06168 -0.0312 0.0072 1.0000
16.500 1.4677 0.07059 0.06582 -0.0320 0.0072 1.0000
16.750 1.4609 0.07500 0.07033 -0.0331 0.0071 1.0000
17.000 1.4527 0.07967 0.07511 -0.0342 0.0071 1.0000
17.250 1.4435 0.08463 0.08017 -0.0356 0.0070 1.0000
17.500 1.4336 0.08975 0.08540 -0.0372 0.0069 1.0000
17.750 1.4229 0.09504 0.09079 -0.0388 0.0069 1.0000
18.000 1.4117 0.10050 0.09635 -0.0407 0.0068 1.0000
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Polar data table (+)
Polar graphs
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