NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 500,000 Max Cl/Cd: 60.53 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20410-il-500000-n5.txt Download as CSV file: xf-sc20410-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0410 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
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0901 0.07627 0.07288 -0.0255 1.0000 0.0128
-15.250 -1.1174 0.06653 0.06291 -0.0322 1.0000 0.0128
-15.000 -1.1357 0.05965 0.05583 -0.0365 1.0000 0.0128
-14.750 -1.1485 0.05434 0.05036 -0.0393 1.0000 0.0129
-14.500 -1.1576 0.04997 0.04583 -0.0412 1.0000 0.0129
-14.250 -1.1632 0.04633 0.04203 -0.0424 1.0000 0.0130
-14.000 -1.1662 0.04317 0.03874 -0.0431 1.0000 0.0130
-13.750 -1.1669 0.04040 0.03583 -0.0435 1.0000 0.0131
-13.500 -1.1654 0.03797 0.03327 -0.0436 1.0000 0.0132
-13.250 -1.1622 0.03578 0.03095 -0.0434 1.0000 0.0133
-13.000 -1.1575 0.03384 0.02888 -0.0430 1.0000 0.0135
-12.750 -1.1518 0.03208 0.02698 -0.0424 1.0000 0.0136
-12.500 -1.1457 0.03049 0.02528 -0.0415 1.0000 0.0137
-12.250 -1.1354 0.02901 0.02367 -0.0410 1.0000 0.0139
-12.000 -1.1213 0.02760 0.02213 -0.0410 1.0000 0.0141
-11.750 -1.1052 0.02631 0.02071 -0.0409 1.0000 0.0143
-11.500 -1.0876 0.02514 0.01942 -0.0407 1.0000 0.0145
-11.250 -1.0690 0.02407 0.01822 -0.0405 1.0000 0.0147
-11.000 -1.0492 0.02307 0.01711 -0.0402 1.0000 0.0149
-10.750 -1.0286 0.02215 0.01608 -0.0400 1.0000 0.0152
-10.500 -1.0070 0.02133 0.01515 -0.0398 1.0000 0.0154
-10.250 -0.9860 0.02031 0.01409 -0.0397 1.0000 0.0158
-10.000 -0.9635 0.01955 0.01327 -0.0396 1.0000 0.0163
-9.750 -0.9402 0.01888 0.01255 -0.0394 1.0000 0.0167
-9.500 -0.9165 0.01823 0.01185 -0.0393 1.0000 0.0171
-9.250 -0.8924 0.01760 0.01116 -0.0392 1.0000 0.0176
-9.000 -0.8680 0.01700 0.01050 -0.0392 1.0000 0.0181
-8.750 -0.8431 0.01643 0.00987 -0.0392 1.0000 0.0187
-8.500 -0.8180 0.01587 0.00925 -0.0392 1.0000 0.0192
-8.250 -0.7926 0.01532 0.00869 -0.0392 1.0000 0.0201
-8.000 -0.7668 0.01486 0.00822 -0.0393 1.0000 0.0211
-7.750 -0.7409 0.01443 0.00776 -0.0393 1.0000 0.0223
-7.500 -0.7148 0.01401 0.00731 -0.0393 1.0000 0.0236
-7.250 -0.6886 0.01362 0.00692 -0.0394 1.0000 0.0254
-7.000 -0.6624 0.01329 0.00658 -0.0394 1.0000 0.0276
-6.750 -0.6360 0.01294 0.00623 -0.0395 1.0000 0.0299
-6.500 -0.6096 0.01264 0.00593 -0.0395 1.0000 0.0324
-6.250 -0.5832 0.01239 0.00565 -0.0395 1.0000 0.0344
-6.000 -0.5565 0.01206 0.00536 -0.0396 1.0000 0.0371
-5.750 -0.5290 0.01181 0.00511 -0.0398 0.9998 0.0397
-5.500 -0.4956 0.01154 0.00482 -0.0412 0.9985 0.0424
-5.250 -0.4622 0.01124 0.00456 -0.0427 0.9971 0.0463
-5.000 -0.4285 0.01103 0.00434 -0.0442 0.9955 0.0502
-4.750 -0.3938 0.01072 0.00409 -0.0460 0.9942 0.0566
-4.500 -0.3601 0.01047 0.00385 -0.0475 0.9918 0.0623
-4.250 -0.3259 0.01019 0.00362 -0.0490 0.9894 0.0697
-4.000 -0.2917 0.00994 0.00341 -0.0506 0.9873 0.0791
-3.750 -0.2571 0.00967 0.00321 -0.0523 0.9856 0.0937
-3.500 -0.2218 0.00934 0.00301 -0.0542 0.9841 0.1198
-3.250 -0.1871 0.00895 0.00282 -0.0561 0.9819 0.1634
-3.000 -0.1525 0.00851 0.00262 -0.0580 0.9790 0.2239
-2.750 -0.1161 0.00792 0.00240 -0.0605 0.9767 0.3162
-2.500 -0.0782 0.00718 0.00214 -0.0635 0.9748 0.4407
-2.250 -0.0408 0.00662 0.00213 -0.0660 0.9729 0.5842
-2.000 -0.0069 0.00656 0.00214 -0.0672 0.9675 0.6161
-1.750 0.0275 0.00652 0.00213 -0.0684 0.9604 0.6336
-1.500 0.0609 0.00652 0.00216 -0.0694 0.9504 0.6535
-1.250 0.0933 0.00654 0.00218 -0.0700 0.9351 0.6666
-1.000 0.1239 0.00656 0.00217 -0.0702 0.9155 0.6749
-0.750 0.1520 0.00661 0.00218 -0.0699 0.8907 0.6800
-0.500 0.1800 0.00671 0.00217 -0.0695 0.8646 0.6862
-0.250 0.2068 0.00684 0.00219 -0.0689 0.8292 0.6916
0.000 0.2333 0.00703 0.00222 -0.0683 0.7824 0.6961
0.250 0.2600 0.00727 0.00223 -0.0677 0.7225 0.6993
0.500 0.2863 0.00765 0.00225 -0.0673 0.6402 0.7018
0.750 0.3113 0.00834 0.00235 -0.0668 0.5003 0.7038
1.000 0.3369 0.00906 0.00253 -0.0667 0.3682 0.7056
1.250 0.3639 0.00952 0.00268 -0.0666 0.2855 0.7073
1.750 0.4186 0.01032 0.00299 -0.0667 0.1632 0.7106
2.000 0.4464 0.01062 0.00315 -0.0667 0.1279 0.7125
2.250 0.4745 0.01088 0.00331 -0.0668 0.1060 0.7144
2.500 0.5027 0.01112 0.00347 -0.0669 0.0878 0.7161
2.750 0.5310 0.01135 0.00365 -0.0670 0.0760 0.7179
3.000 0.5591 0.01159 0.00384 -0.0670 0.0667 0.7196
3.250 0.5874 0.01181 0.00404 -0.0671 0.0609 0.7213
3.500 0.6153 0.01205 0.00425 -0.0671 0.0548 0.7229
3.750 0.6431 0.01226 0.00447 -0.0671 0.0501 0.7244
4.000 0.6707 0.01253 0.00472 -0.0670 0.0461 0.7261
4.250 0.6985 0.01275 0.00498 -0.0669 0.0434 0.7281
4.500 0.7261 0.01300 0.00522 -0.0669 0.0401 0.7302
4.750 0.7536 0.01329 0.00551 -0.0668 0.0373 0.7323
5.000 0.7812 0.01354 0.00579 -0.0668 0.0346 0.7343
5.250 0.8084 0.01386 0.00609 -0.0667 0.0321 0.7363
5.500 0.8358 0.01416 0.00642 -0.0666 0.0300 0.7383
5.750 0.8628 0.01447 0.00676 -0.0664 0.0277 0.7401
6.000 0.8893 0.01484 0.00715 -0.0662 0.0257 0.7420
6.250 0.9160 0.01519 0.00755 -0.0659 0.0241 0.7440
6.500 0.9424 0.01557 0.00797 -0.0657 0.0226 0.7461
6.750 0.9684 0.01603 0.00844 -0.0654 0.0212 0.7484
7.000 0.9946 0.01645 0.00892 -0.0651 0.0203 0.7508
7.250 1.0206 0.01689 0.00941 -0.0648 0.0193 0.7533
7.500 1.0463 0.01737 0.00992 -0.0645 0.0185 0.7556
7.750 1.0714 0.01790 0.01051 -0.0640 0.0179 0.7577
8.000 1.0956 0.01855 0.01122 -0.0635 0.0173 0.7600
8.250 1.1202 0.01914 0.01190 -0.0630 0.0170 0.7628
8.500 1.1445 0.01976 0.01263 -0.0624 0.0166 0.7658
8.750 1.1685 0.02043 0.01339 -0.0618 0.0163 0.7688
9.000 1.1921 0.02113 0.01417 -0.0612 0.0159 0.7717
9.250 1.2151 0.02184 0.01499 -0.0605 0.0156 0.7742
9.500 1.2377 0.02259 0.01586 -0.0598 0.0153 0.7770
9.750 1.2599 0.02337 0.01674 -0.0590 0.0150 0.7800
10.000 1.2815 0.02421 0.01767 -0.0581 0.0148 0.7832
10.250 1.3024 0.02512 0.01868 -0.0572 0.0145 0.7865
10.500 1.3216 0.02617 0.01985 -0.0561 0.0142 0.7893
10.750 1.3384 0.02751 0.02132 -0.0547 0.0139 0.7925
11.000 1.3571 0.02854 0.02252 -0.0535 0.0138 0.7960
11.250 1.3745 0.02968 0.02383 -0.0522 0.0136 0.7997
11.500 1.3900 0.03097 0.02530 -0.0507 0.0134 0.8033
11.750 1.4037 0.03236 0.02689 -0.0490 0.0133 0.8070
12.000 1.4153 0.03386 0.02861 -0.0471 0.0131 0.8111
12.250 1.4246 0.03549 0.03043 -0.0450 0.0130 0.8154
12.500 1.4307 0.03721 0.03236 -0.0426 0.0128 0.8192
12.750 1.4303 0.03900 0.03434 -0.0393 0.0127 0.8235
13.000 1.4264 0.04099 0.03653 -0.0359 0.0127 0.8283
13.250 1.4208 0.04337 0.03912 -0.0331 0.0126 0.8329
13.500 1.4129 0.04616 0.04212 -0.0309 0.0125 0.8376
13.750 1.4020 0.04960 0.04577 -0.0296 0.0124 0.8426
14.000 1.3880 0.05386 0.05026 -0.0295 0.0124 0.8474
14.250 1.3688 0.05948 0.05612 -0.0310 0.0124 0.8521
14.500 1.3429 0.06744 0.06435 -0.0355 0.0124 0.8568
14.750 1.2962 0.08272 0.07998 -0.0472 0.0125 0.8597
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