CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il) Reynolds number: 500,000 Max Cl/Cd: 66.8 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cast102-il-500000-n5.txt Download as CSV file: xf-cast102-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CAST 10-2/DOA 2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5048 0.07849 0.07610 -0.0616 0.9896 0.0099
-10.000 -0.5229 0.06909 0.06660 -0.0709 0.9820 0.0097
-9.750 -0.5402 0.06250 0.05985 -0.0759 0.9730 0.0097
-9.500 -0.5560 0.05785 0.05504 -0.0763 0.9623 0.0096
-9.250 -0.5626 0.05344 0.05043 -0.0760 0.9551 0.0097
-9.000 -0.5650 0.04928 0.04605 -0.0751 0.9483 0.0097
-8.750 -0.5629 0.04522 0.04173 -0.0740 0.9436 0.0098
-8.500 -0.5579 0.04126 0.03750 -0.0727 0.9384 0.0099
-8.250 -0.5500 0.03735 0.03329 -0.0712 0.9338 0.0100
-8.000 -0.5385 0.03376 0.02936 -0.0697 0.9301 0.0103
-7.750 -0.5256 0.02959 0.02477 -0.0681 0.9265 0.0108
-7.500 -0.5105 0.02553 0.02024 -0.0665 0.9229 0.0110
-7.250 -0.4916 0.02204 0.01623 -0.0651 0.9199 0.0114
-7.000 -0.4693 0.02014 0.01404 -0.0645 0.9173 0.0117
-6.750 -0.4454 0.01909 0.01287 -0.0642 0.9149 0.0119
-6.500 -0.4205 0.01827 0.01195 -0.0640 0.9126 0.0122
-6.250 -0.3953 0.01749 0.01109 -0.0639 0.9100 0.0125
-6.000 -0.3698 0.01672 0.01023 -0.0637 0.9075 0.0128
-5.750 -0.3443 0.01602 0.00944 -0.0635 0.9051 0.0132
-5.500 -0.3186 0.01538 0.00872 -0.0633 0.9027 0.0139
-5.250 -0.2930 0.01474 0.00799 -0.0630 0.9005 0.0144
-5.000 -0.2673 0.01415 0.00730 -0.0628 0.8986 0.0148
-4.750 -0.2427 0.01341 0.00654 -0.0625 0.8963 0.0152
-4.500 -0.2173 0.01291 0.00603 -0.0624 0.8939 0.0156
-4.250 -0.1912 0.01250 0.00562 -0.0623 0.8914 0.0162
-4.000 -0.1649 0.01212 0.00521 -0.0623 0.8890 0.0167
-3.750 -0.1384 0.01175 0.00483 -0.0623 0.8868 0.0174
-3.500 -0.1112 0.01148 0.00452 -0.0623 0.8850 0.0184
-3.250 -0.0842 0.01113 0.00414 -0.0624 0.8833 0.0193
-3.000 -0.0570 0.01083 0.00385 -0.0626 0.8812 0.0202
-2.750 -0.0295 0.01060 0.00362 -0.0627 0.8787 0.0213
-2.500 -0.0017 0.01039 0.00340 -0.0629 0.8763 0.0226
-2.250 0.0264 0.01021 0.00321 -0.0631 0.8741 0.0240
-2.000 0.0544 0.01001 0.00301 -0.0634 0.8722 0.0272
-1.750 0.0828 0.00986 0.00284 -0.0636 0.8704 0.0312
-1.250 0.1315 0.00747 0.00234 -0.0643 0.8662 0.5975
-1.000 0.1593 0.00741 0.00238 -0.0643 0.8626 0.6374
-0.750 0.1873 0.00735 0.00235 -0.0643 0.8572 0.6577
-0.500 0.2154 0.00729 0.00229 -0.0642 0.8507 0.6731
-0.250 0.2432 0.00725 0.00226 -0.0642 0.8429 0.6842
0.000 0.2714 0.00721 0.00220 -0.0642 0.8355 0.6932
0.250 0.2995 0.00717 0.00212 -0.0642 0.8252 0.6975
0.500 0.3274 0.00713 0.00207 -0.0642 0.8138 0.7005
0.750 0.3553 0.00710 0.00202 -0.0642 0.8011 0.7038
1.000 0.3833 0.00709 0.00198 -0.0642 0.7876 0.7074
1.250 0.4115 0.00710 0.00197 -0.0643 0.7750 0.7113
1.500 0.4392 0.00712 0.00196 -0.0642 0.7565 0.7148
1.750 0.4661 0.00717 0.00194 -0.0640 0.7288 0.7185
2.000 0.4910 0.00735 0.00194 -0.0633 0.6794 0.7225
2.250 0.5083 0.00804 0.00211 -0.0613 0.5682 0.7265
2.500 0.5239 0.00893 0.00246 -0.0591 0.4469 0.7304
2.750 0.5439 0.00955 0.00274 -0.0579 0.3664 0.7348
3.000 0.5673 0.00995 0.00294 -0.0573 0.3212 0.7397
3.500 0.6167 0.01052 0.00332 -0.0565 0.2620 0.7487
3.750 0.6414 0.01081 0.00352 -0.0561 0.2354 0.7536
4.000 0.6660 0.01112 0.00373 -0.0557 0.2108 0.7588
4.250 0.6905 0.01139 0.00394 -0.0553 0.1897 0.7640
4.500 0.7152 0.01166 0.00416 -0.0549 0.1722 0.7700
4.750 0.7400 0.01193 0.00439 -0.0545 0.1574 0.7759
5.000 0.7646 0.01218 0.00463 -0.0541 0.1447 0.7818
5.250 0.7894 0.01243 0.00488 -0.0538 0.1337 0.7884
5.500 0.8139 0.01268 0.00513 -0.0533 0.1247 0.7950
5.750 0.8382 0.01295 0.00540 -0.0529 0.1144 0.8029
6.000 0.8620 0.01324 0.00568 -0.0523 0.1016 0.8109
6.250 0.8857 0.01354 0.00597 -0.0518 0.0904 0.8199
6.500 0.9088 0.01385 0.00628 -0.0511 0.0796 0.8292
6.750 0.9315 0.01420 0.00663 -0.0504 0.0679 0.8397
7.750 1.0108 0.01594 0.00843 -0.0450 0.0259 0.9162
8.000 1.0310 0.01632 0.00889 -0.0437 0.0236 0.9757
8.250 1.0535 0.01678 0.00938 -0.0431 0.0221 1.0000
8.500 1.0754 0.01725 0.00991 -0.0424 0.0211 1.0000
8.750 1.0966 0.01776 0.01047 -0.0415 0.0201 1.0000
9.000 1.1162 0.01832 0.01107 -0.0403 0.0192 1.0000
9.250 1.1342 0.01900 0.01179 -0.0390 0.0183 1.0000
9.500 1.1519 0.01968 0.01254 -0.0375 0.0177 1.0000
9.750 1.1708 0.02024 0.01317 -0.0363 0.0171 1.0000
10.000 1.1890 0.02085 0.01385 -0.0350 0.0165 1.0000
10.250 1.2065 0.02151 0.01458 -0.0337 0.0159 1.0000
10.500 1.2233 0.02222 0.01535 -0.0323 0.0154 1.0000
10.750 1.2392 0.02298 0.01619 -0.0308 0.0150 1.0000
11.000 1.2539 0.02383 0.01710 -0.0292 0.0146 1.0000
11.250 1.2661 0.02486 0.01819 -0.0273 0.0142 1.0000
11.500 1.2759 0.02605 0.01947 -0.0251 0.0138 1.0000
11.750 1.2893 0.02698 0.02050 -0.0235 0.0136 1.0000
12.000 1.3016 0.02799 0.02163 -0.0218 0.0134 1.0000
12.250 1.3125 0.02910 0.02284 -0.0200 0.0131 1.0000
12.500 1.3227 0.03028 0.02413 -0.0183 0.0129 1.0000
12.750 1.3321 0.03152 0.02548 -0.0165 0.0126 1.0000
13.000 1.3410 0.03280 0.02687 -0.0148 0.0123 1.0000
13.250 1.3492 0.03416 0.02833 -0.0131 0.0120 1.0000
13.500 1.3563 0.03561 0.02989 -0.0115 0.0118 1.0000
13.750 1.3623 0.03719 0.03157 -0.0099 0.0116 1.0000
14.000 1.3667 0.03895 0.03345 -0.0084 0.0114 1.0000
14.250 1.3695 0.04089 0.03549 -0.0069 0.0112 1.0000
14.500 1.3702 0.04308 0.03780 -0.0055 0.0111 1.0000
14.750 1.3687 0.04559 0.04042 -0.0043 0.0110 1.0000
15.000 1.3642 0.04850 0.04346 -0.0032 0.0108 1.0000
15.250 1.3565 0.05191 0.04701 -0.0024 0.0107 1.0000
15.500 1.3502 0.05543 0.05067 -0.0021 0.0106 1.0000
15.750 1.3441 0.05919 0.05460 -0.0024 0.0105 1.0000
16.000 1.3364 0.06343 0.05901 -0.0032 0.0105 1.0000
16.250 1.3264 0.06837 0.06412 -0.0047 0.0104 1.0000
16.500 1.3149 0.07397 0.06989 -0.0070 0.0104 1.0000
16.750 1.3010 0.08033 0.07643 -0.0100 0.0103 1.0000
17.000 1.2852 0.08739 0.08367 -0.0137 0.0103 1.0000
17.250 1.2675 0.09507 0.09151 -0.0178 0.0103 1.0000
17.500 1.2482 0.10317 0.09978 -0.0222 0.0103 1.0000
17.750 1.2278 0.11150 0.10826 -0.0267 0.0102 1.0000
18.000 1.2068 0.12009 0.11699 -0.0314 0.0102 1.0000
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