SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 100,000 Max Cl/Cd: 56.3 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2030-il-100000.txt Download as CSV file: xf-sd2030-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD2030-086-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4436 0.09455 0.08968 -0.0330 1.0000 0.1002
-8.250 -0.4693 0.09274 0.08802 -0.0351 1.0000 0.1012
-8.000 -0.4945 0.09030 0.08568 -0.0383 1.0000 0.1016
-7.750 -0.4720 0.08568 0.08109 -0.0321 1.0000 0.1044
-7.500 -0.4678 0.08305 0.07849 -0.0296 1.0000 0.1080
-7.250 -0.4765 0.08019 0.07569 -0.0299 1.0000 0.1111
-7.000 -0.5008 0.07728 0.07274 -0.0345 1.0000 0.1152
-6.750 -0.5063 0.07320 0.06866 -0.0342 1.0000 0.1173
-6.500 -0.4965 0.07055 0.06612 -0.0301 1.0000 0.1206
-6.250 -0.4967 0.06777 0.06331 -0.0296 1.0000 0.1261
-6.000 -0.5015 0.06387 0.05927 -0.0312 1.0000 0.1324
-5.750 -0.4939 0.06137 0.05682 -0.0286 1.0000 0.1371
-5.500 -0.4912 0.05786 0.05315 -0.0295 1.0000 0.1473
-5.250 -0.4843 0.05523 0.05029 -0.0298 1.0000 0.1601
-5.000 -0.4737 0.05257 0.04778 -0.0270 1.0000 0.1669
-4.750 -0.4646 0.05003 0.04501 -0.0274 1.0000 0.1893
-4.500 -0.4534 0.04745 0.04245 -0.0258 1.0000 0.2051
-4.250 -0.4039 0.03493 0.02797 -0.0315 1.0000 0.0902
-4.000 -0.3761 0.03106 0.02324 -0.0304 1.0000 0.0729
-3.750 -0.3523 0.02820 0.02004 -0.0300 1.0000 0.0703
-3.500 -0.3274 0.02601 0.01743 -0.0292 1.0000 0.0686
-3.250 -0.3025 0.02427 0.01531 -0.0284 1.0000 0.0683
-3.000 -0.2784 0.02313 0.01387 -0.0275 1.0000 0.0719
-2.750 -0.2543 0.02189 0.01242 -0.0267 1.0000 0.0753
-2.500 -0.2310 0.02070 0.01124 -0.0259 1.0000 0.0793
-2.250 -0.2078 0.01986 0.01034 -0.0249 1.0000 0.0860
-2.000 -0.1850 0.01896 0.00951 -0.0240 1.0000 0.1016
-1.750 -0.1617 0.01762 0.00866 -0.0234 1.0000 0.1648
-1.500 -0.1327 0.01458 0.00876 -0.0216 1.0000 1.0000
-1.250 -0.1122 0.01475 0.00859 -0.0208 1.0000 1.0000
-1.000 -0.0916 0.01496 0.00854 -0.0201 1.0000 1.0000
-0.750 -0.0709 0.01521 0.00855 -0.0195 1.0000 1.0000
-0.500 -0.0503 0.01548 0.00864 -0.0189 1.0000 1.0000
-0.250 -0.0297 0.01579 0.00876 -0.0184 1.0000 1.0000
0.000 0.0081 0.01642 0.00921 -0.0212 0.9946 1.0000
0.250 0.0520 0.01706 0.00969 -0.0251 0.9856 1.0000
0.500 0.0937 0.01762 0.01012 -0.0285 0.9759 1.0000
0.750 0.1357 0.01816 0.01056 -0.0319 0.9662 1.0000
1.000 0.1829 0.01873 0.01106 -0.0362 0.9572 1.0000
1.250 0.2213 0.01903 0.01131 -0.0387 0.9453 1.0000
1.500 0.2611 0.01931 0.01157 -0.0413 0.9333 1.0000
1.750 0.3023 0.01953 0.01179 -0.0441 0.9213 1.0000
2.000 0.3449 0.01965 0.01193 -0.0469 0.9093 1.0000
2.250 0.3898 0.01965 0.01196 -0.0499 0.8974 1.0000
2.500 0.4429 0.01942 0.01183 -0.0541 0.8869 1.0000
2.750 0.4867 0.01909 0.01159 -0.0565 0.8735 1.0000
3.000 0.5323 0.01860 0.01122 -0.0589 0.8600 1.0000
3.250 0.5782 0.01796 0.01073 -0.0611 0.8464 1.0000
3.500 0.6223 0.01719 0.01010 -0.0627 0.8318 1.0000
3.750 0.6621 0.01643 0.00947 -0.0633 0.8144 1.0000
4.000 0.6956 0.01577 0.00898 -0.0628 0.7917 1.0000
4.250 0.7281 0.01515 0.00845 -0.0620 0.7642 1.0000
4.500 0.7584 0.01463 0.00798 -0.0608 0.7286 1.0000
4.750 0.7841 0.01437 0.00774 -0.0590 0.6799 1.0000
5.000 0.8084 0.01436 0.00754 -0.0570 0.6149 1.0000
5.250 0.8280 0.01478 0.00759 -0.0545 0.5337 1.0000
5.500 0.8434 0.01559 0.00793 -0.0518 0.4516 1.0000
5.750 0.8575 0.01658 0.00848 -0.0492 0.3781 1.0000
6.000 0.8717 0.01768 0.00920 -0.0468 0.3163 1.0000
6.250 0.8868 0.01882 0.01002 -0.0447 0.2630 1.0000
6.500 0.9030 0.02004 0.01096 -0.0428 0.2207 1.0000
6.750 0.9204 0.02131 0.01196 -0.0412 0.1882 1.0000
7.000 0.9398 0.02255 0.01310 -0.0399 0.1624 1.0000
7.250 0.9614 0.02400 0.01448 -0.0389 0.1434 1.0000
7.500 0.9830 0.02533 0.01583 -0.0379 0.1273 1.0000
7.750 1.0073 0.02700 0.01750 -0.0374 0.1152 1.0000
8.000 1.0304 0.02868 0.01917 -0.0368 0.1036 1.0000
8.250 1.0525 0.03026 0.02089 -0.0358 0.0936 1.0000
8.500 1.0713 0.03196 0.02285 -0.0344 0.0833 1.0000
8.750 1.0894 0.03401 0.02512 -0.0331 0.0737 1.0000
9.000 1.1064 0.03633 0.02751 -0.0319 0.0650 1.0000
9.250 1.1202 0.03846 0.03006 -0.0297 0.0585 1.0000
9.500 1.1340 0.04214 0.03386 -0.0284 0.0537 1.0000
9.750 1.1380 0.04482 0.03719 -0.0251 0.0508 1.0000
10.000 1.1425 0.04758 0.04034 -0.0224 0.0476 1.0000
10.250 1.1456 0.05087 0.04396 -0.0199 0.0461 1.0000
10.500 1.1447 0.05442 0.04782 -0.0172 0.0454 1.0000
10.750 1.1360 0.05826 0.05201 -0.0141 0.0451 1.0000
11.000 1.1094 0.06230 0.05649 -0.0095 0.0459 1.0000
11.250 1.0806 0.06669 0.06122 -0.0064 0.0466 1.0000
11.500 1.0498 0.07179 0.06661 -0.0051 0.0476 1.0000
11.750 1.0190 0.07767 0.07271 -0.0059 0.0484 1.0000
12.000 0.9894 0.08453 0.07973 -0.0089 0.0496 1.0000
12.250 0.9606 0.09279 0.08810 -0.0140 0.0508 1.0000
12.500 0.9369 0.10192 0.09728 -0.0200 0.0521 1.0000
12.750 0.9201 0.11089 0.10625 -0.0252 0.0532 1.0000
13.000 0.9100 0.11883 0.11417 -0.0288 0.0540 1.0000
13.250 0.7067 0.14902 0.14463 -0.0424 0.1315 1.0000
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Polar data table (+)
Polar graphs
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