NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.2 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rcsc2-il-1000000.txt Download as CSV file: xf-rcsc2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-SC2 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8655 0.06057 0.05826 -0.0506 1.0000 0.0189
-12.500 -0.9032 0.05159 0.04906 -0.0572 1.0000 0.0188
-12.250 -0.9338 0.04597 0.04321 -0.0582 1.0000 0.0187
-12.000 -0.9604 0.04190 0.03892 -0.0560 1.0000 0.0186
-11.750 -0.9855 0.03910 0.03592 -0.0508 1.0000 0.0185
-11.500 -1.0085 0.03698 0.03362 -0.0441 1.0000 0.0185
-11.250 -1.0253 0.03478 0.03121 -0.0381 1.0000 0.0184
-11.000 -1.0352 0.03263 0.02884 -0.0329 1.0000 0.0184
-10.750 -1.0392 0.03061 0.02660 -0.0284 1.0000 0.0184
-10.500 -1.0381 0.02879 0.02457 -0.0245 1.0000 0.0184
-10.250 -1.0331 0.02717 0.02276 -0.0212 1.0000 0.0185
-10.000 -1.0174 0.02551 0.02089 -0.0198 0.9994 0.0186
-9.750 -0.9941 0.02418 0.01938 -0.0199 0.9983 0.0188
-9.500 -0.9689 0.02312 0.01817 -0.0201 0.9972 0.0190
-9.250 -0.9432 0.02203 0.01692 -0.0203 0.9962 0.0191
-9.000 -0.9162 0.02109 0.01585 -0.0207 0.9953 0.0192
-8.750 -0.8879 0.02035 0.01500 -0.0212 0.9946 0.0193
-8.500 -0.8644 0.01863 0.01312 -0.0211 0.9936 0.0195
-8.250 -0.8407 0.01737 0.01177 -0.0208 0.9920 0.0198
-8.000 -0.8146 0.01649 0.01085 -0.0208 0.9906 0.0200
-7.750 -0.7872 0.01580 0.01013 -0.0211 0.9894 0.0202
-7.500 -0.7590 0.01522 0.00952 -0.0215 0.9883 0.0205
-7.250 -0.7298 0.01468 0.00895 -0.0220 0.9873 0.0207
-7.000 -0.6998 0.01417 0.00840 -0.0227 0.9864 0.0210
-6.750 -0.6691 0.01368 0.00789 -0.0236 0.9857 0.0213
-6.500 -0.6377 0.01322 0.00740 -0.0245 0.9850 0.0216
-6.250 -0.6060 0.01279 0.00694 -0.0255 0.9844 0.0220
-6.000 -0.5821 0.01242 0.00655 -0.0247 0.9816 0.0224
-5.750 -0.5542 0.01207 0.00618 -0.0249 0.9797 0.0227
-5.500 -0.5244 0.01181 0.00590 -0.0253 0.9783 0.0231
-5.250 -0.4959 0.01118 0.00526 -0.0257 0.9770 0.0241
-5.000 -0.4647 0.01084 0.00492 -0.0265 0.9761 0.0249
-4.750 -0.4320 0.01055 0.00463 -0.0276 0.9753 0.0258
-4.500 -0.3981 0.01027 0.00434 -0.0290 0.9746 0.0268
-4.250 -0.3640 0.00997 0.00404 -0.0304 0.9740 0.0280
-4.000 -0.3308 0.00964 0.00373 -0.0316 0.9732 0.0302
-3.750 -0.2993 0.00943 0.00352 -0.0324 0.9718 0.0324
-3.500 -0.2756 0.00917 0.00331 -0.0314 0.9676 0.0368
-3.250 -0.2458 0.00888 0.00311 -0.0318 0.9653 0.0493
-3.000 -0.2159 0.00860 0.00295 -0.0323 0.9635 0.0696
-2.750 -0.1860 0.00834 0.00280 -0.0327 0.9618 0.0908
-2.500 -0.1559 0.00804 0.00265 -0.0332 0.9601 0.1262
-2.250 -0.1320 0.00774 0.00251 -0.0322 0.9549 0.1646
-2.000 -0.1066 0.00732 0.00231 -0.0316 0.9496 0.2219
-1.750 -0.0808 0.00682 0.00210 -0.0311 0.9455 0.3036
-1.500 -0.0619 0.00615 0.00193 -0.0293 0.9383 0.4427
-1.250 -0.0398 0.00553 0.00174 -0.0280 0.9326 0.5660
-1.000 -0.0176 0.00515 0.00164 -0.0265 0.9254 0.6472
-0.750 0.0058 0.00480 0.00154 -0.0253 0.9189 0.7209
-0.500 0.0301 0.00458 0.00150 -0.0242 0.9117 0.7722
-0.250 0.0554 0.00440 0.00141 -0.0232 0.9001 0.8092
0.000 0.0811 0.00429 0.00136 -0.0223 0.8862 0.8368
0.250 0.1073 0.00425 0.00134 -0.0216 0.8712 0.8604
0.500 0.1328 0.00423 0.00134 -0.0206 0.8497 0.8829
0.750 0.1581 0.00428 0.00134 -0.0196 0.8219 0.9004
1.000 0.1828 0.00440 0.00136 -0.0186 0.7847 0.9137
1.250 0.2058 0.00461 0.00140 -0.0172 0.7356 0.9260
1.500 0.2274 0.00495 0.00151 -0.0154 0.6671 0.9370
1.750 0.2469 0.00545 0.00164 -0.0135 0.5688 0.9463
2.000 0.2643 0.00619 0.00184 -0.0113 0.4272 0.9562
2.250 0.2871 0.00687 0.00205 -0.0103 0.3108 0.9634
2.500 0.3121 0.00726 0.00221 -0.0097 0.2532 0.9705
2.750 0.3411 0.00763 0.00236 -0.0100 0.1989 0.9738
3.000 0.3731 0.00797 0.00251 -0.0110 0.1606 0.9760
3.250 0.4049 0.00830 0.00267 -0.0120 0.1249 0.9783
3.500 0.4369 0.00861 0.00283 -0.0130 0.0978 0.9807
3.750 0.4664 0.00886 0.00300 -0.0134 0.0811 0.9842
4.000 0.5015 0.00912 0.00317 -0.0151 0.0675 0.9851
4.250 0.5359 0.00940 0.00336 -0.0166 0.0546 0.9862
4.500 0.5691 0.00974 0.00358 -0.0179 0.0370 0.9876
4.750 0.6017 0.01008 0.00385 -0.0191 0.0301 0.9892
5.000 0.6340 0.01042 0.00416 -0.0201 0.0271 0.9912
5.250 0.6660 0.01069 0.00444 -0.0211 0.0257 0.9934
5.500 0.6988 0.01100 0.00473 -0.0222 0.0245 0.9948
5.750 0.7314 0.01142 0.00516 -0.0234 0.0234 0.9959
6.000 0.7634 0.01181 0.00557 -0.0244 0.0228 0.9972
6.250 0.7951 0.01213 0.00590 -0.0254 0.0224 0.9984
6.500 0.8262 0.01249 0.00628 -0.0263 0.0219 0.9996
6.750 0.8500 0.01284 0.00666 -0.0255 0.0216 1.0000
7.000 0.8686 0.01318 0.00701 -0.0237 0.0212 1.0000
7.250 0.8870 0.01351 0.00737 -0.0219 0.0209 1.0000
7.500 0.9052 0.01387 0.00775 -0.0200 0.0206 1.0000
7.750 0.9230 0.01427 0.00816 -0.0180 0.0203 1.0000
8.000 0.9404 0.01471 0.00863 -0.0160 0.0201 1.0000
8.250 0.9574 0.01521 0.00916 -0.0139 0.0199 1.0000
8.500 0.9742 0.01578 0.00976 -0.0118 0.0198 1.0000
8.750 0.9906 0.01643 0.01045 -0.0097 0.0196 1.0000
9.000 1.0068 0.01718 0.01125 -0.0076 0.0195 1.0000
9.250 1.0230 0.01804 0.01217 -0.0056 0.0193 1.0000
9.500 1.0391 0.01904 0.01324 -0.0036 0.0192 1.0000
9.750 1.0556 0.02018 0.01445 -0.0017 0.0192 1.0000
10.000 1.0742 0.02096 0.01530 -0.0003 0.0191 1.0000
10.250 1.0927 0.02176 0.01617 0.0012 0.0191 1.0000
10.500 1.1110 0.02260 0.01710 0.0026 0.0190 1.0000
10.750 1.1287 0.02349 0.01808 0.0041 0.0190 1.0000
11.000 1.1457 0.02445 0.01914 0.0056 0.0190 1.0000
11.250 1.1617 0.02547 0.02027 0.0072 0.0189 1.0000
11.500 1.1766 0.02658 0.02149 0.0090 0.0189 1.0000
11.750 1.1902 0.02774 0.02278 0.0108 0.0188 1.0000
12.000 1.2020 0.02900 0.02417 0.0129 0.0188 1.0000
12.250 1.2115 0.03034 0.02565 0.0152 0.0187 1.0000
12.500 1.2167 0.03171 0.02717 0.0181 0.0187 1.0000
12.750 1.2192 0.03323 0.02884 0.0212 0.0186 1.0000
13.000 1.2193 0.03494 0.03070 0.0243 0.0186 1.0000
13.250 1.2168 0.03688 0.03281 0.0272 0.0186 1.0000
13.500 1.2114 0.03909 0.03520 0.0300 0.0186 1.0000
13.750 1.2030 0.04168 0.03796 0.0324 0.0185 1.0000
14.000 1.1912 0.04476 0.04123 0.0342 0.0185 1.0000
14.250 1.1760 0.04850 0.04516 0.0351 0.0186 1.0000
14.500 1.1569 0.05319 0.05004 0.0346 0.0186 1.0000
14.750 1.1334 0.05922 0.05628 0.0323 0.0186 1.0000
15.000 1.1043 0.06737 0.06464 0.0273 0.0187 1.0000
15.250 1.0629 0.07979 0.07730 0.0180 0.0188 1.0000
15.500 0.9697 0.10531 0.10313 0.0009 0.0192 1.0000
15.750 0.7646 0.11215 0.11019 0.0089 0.0197 1.0000
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