NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 500,000 Max Cl/Cd: 53.61 at α=-0.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20606-il-500000-n5.txt Download as CSV file: xf-sc20606-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0606 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6488 0.08096 0.07867 -0.0142 1.0000 0.0070
-9.500 -0.6594 0.07431 0.07207 -0.0186 1.0000 0.0069
-9.250 -0.6765 0.06145 0.05920 -0.0334 1.0000 0.0067
-9.000 -0.6822 0.05224 0.04979 -0.0400 1.0000 0.0067
-8.750 -0.6786 0.04439 0.04164 -0.0440 1.0000 0.0068
-8.500 -0.6677 0.03648 0.03330 -0.0473 1.0000 0.0070
-8.250 -0.6486 0.02938 0.02562 -0.0503 1.0000 0.0073
-8.000 -0.6245 0.02666 0.02259 -0.0515 1.0000 0.0077
-7.750 -0.5984 0.02384 0.01938 -0.0528 1.0000 0.0083
-7.500 -0.5698 0.02032 0.01535 -0.0544 1.0000 0.0085
-7.250 -0.5412 0.01791 0.01256 -0.0554 1.0000 0.0087
-7.000 -0.5130 0.01622 0.01060 -0.0560 1.0000 0.0091
-6.750 -0.4849 0.01499 0.00916 -0.0565 1.0000 0.0096
-6.500 -0.4571 0.01406 0.00808 -0.0568 1.0000 0.0100
-6.250 -0.4293 0.01333 0.00721 -0.0571 1.0000 0.0103
-6.000 -0.4000 0.01235 0.00610 -0.0579 1.0000 0.0107
-5.750 -0.3699 0.01145 0.00510 -0.0588 1.0000 0.0116
-5.500 -0.3416 0.01100 0.00462 -0.0592 1.0000 0.0128
-5.250 -0.3129 0.01057 0.00414 -0.0596 1.0000 0.0138
-5.000 -0.2840 0.01018 0.00366 -0.0601 1.0000 0.0149
-4.750 -0.2554 0.00986 0.00329 -0.0604 1.0000 0.0166
-4.500 -0.2262 0.00952 0.00295 -0.0609 1.0000 0.0224
-4.250 -0.1980 0.00929 0.00273 -0.0611 1.0000 0.0307
-4.000 -0.1699 0.00910 0.00257 -0.0614 1.0000 0.0408
-3.750 -0.1411 0.00887 0.00241 -0.0618 1.0000 0.0618
-3.500 -0.1104 0.00848 0.00225 -0.0629 1.0000 0.1163
-3.250 -0.0785 0.00805 0.00212 -0.0642 1.0000 0.1987
-3.000 -0.0456 0.00761 0.00200 -0.0658 1.0000 0.2987
-2.750 -0.0107 0.00708 0.00191 -0.0680 1.0000 0.4289
-2.500 0.0227 0.00672 0.00193 -0.0695 1.0000 0.5455
-2.250 0.0527 0.00659 0.00200 -0.0701 1.0000 0.6055
-2.000 0.0814 0.00656 0.00208 -0.0704 1.0000 0.6395
-1.750 0.1097 0.00656 0.00215 -0.0705 1.0000 0.6640
-1.500 0.1392 0.00656 0.00221 -0.0709 0.9993 0.6795
-1.250 0.1825 0.00638 0.00209 -0.0743 0.9929 0.6957
-1.000 0.2244 0.00620 0.00198 -0.0773 0.9848 0.7128
-0.750 0.2640 0.00602 0.00187 -0.0797 0.9723 0.7253
-0.500 0.3068 0.00581 0.00172 -0.0828 0.9480 0.7342
-0.250 0.3415 0.00637 0.00151 -0.0833 0.7318 0.7418
0.000 0.3615 0.00758 0.00176 -0.0817 0.4884 0.7493
0.250 0.3866 0.00830 0.00196 -0.0814 0.3434 0.7564
0.500 0.4125 0.00890 0.00215 -0.0813 0.2283 0.7630
0.750 0.4388 0.00946 0.00236 -0.0812 0.1323 0.7696
1.000 0.4652 0.00996 0.00258 -0.0810 0.0645 0.7761
1.250 0.4926 0.01025 0.00281 -0.0810 0.0421 0.7826
1.500 0.5198 0.01048 0.00304 -0.0808 0.0312 0.7881
1.750 0.5472 0.01075 0.00330 -0.0807 0.0226 0.7944
2.000 0.5741 0.01112 0.00368 -0.0804 0.0163 0.8007
2.250 0.6013 0.01145 0.00407 -0.0802 0.0148 0.8080
2.500 0.6280 0.01184 0.00458 -0.0798 0.0136 0.8140
2.750 0.6545 0.01230 0.00512 -0.0794 0.0128 0.8200
3.000 0.6810 0.01273 0.00559 -0.0791 0.0117 0.8257
3.250 0.7067 0.01338 0.00632 -0.0786 0.0107 0.8322
3.500 0.7312 0.01456 0.00766 -0.0778 0.0101 0.8384
3.750 0.7568 0.01524 0.00848 -0.0773 0.0098 0.8447
4.000 0.7825 0.01603 0.00941 -0.0768 0.0095 0.8513
4.250 0.8076 0.01701 0.01057 -0.0761 0.0092 0.8578
4.500 0.8328 0.01829 0.01206 -0.0754 0.0087 0.8641
4.750 0.8568 0.01993 0.01399 -0.0744 0.0084 0.8696
5.000 0.8800 0.02214 0.01656 -0.0733 0.0082 0.8758
5.250 0.9013 0.02487 0.01974 -0.0718 0.0080 0.8818
5.500 0.9227 0.02696 0.02219 -0.0707 0.0075 0.8888
5.750 0.9436 0.02870 0.02420 -0.0696 0.0071 0.8958
6.000 0.9601 0.03223 0.02817 -0.0678 0.0068 0.9034
6.250 0.9726 0.03682 0.03323 -0.0656 0.0066 0.9116
6.500 0.9812 0.04237 0.03923 -0.0634 0.0064 0.9212
6.750 0.9819 0.04978 0.04710 -0.0609 0.0062 0.9344
7.000 0.9740 0.05880 0.05654 -0.0588 0.0061 0.9673
7.250 0.9654 0.06845 0.06646 -0.0592 0.0060 1.0000
7.500 0.9604 0.07598 0.07416 -0.0608 0.0060 1.0000
7.750 0.9517 0.08325 0.08152 -0.0637 0.0060 1.0000
8.000 0.9409 0.08936 0.08770 -0.0667 0.0060 1.0000
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Polar data table (+)
Polar graphs
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