NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Reynolds number: 500,000 Max Cl/Cd: 56.35 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rcsc2-il-500000-n5.txt Download as CSV file: xf-rcsc2-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9596 0.06317 0.05971 -0.0483 1.0000 0.0161
-13.750 -0.9870 0.05446 0.05074 -0.0552 1.0000 0.0161
-13.500 -1.0075 0.04868 0.04474 -0.0583 1.0000 0.0161
-13.250 -1.0232 0.04448 0.04035 -0.0590 1.0000 0.0162
-13.000 -1.0343 0.04133 0.03702 -0.0583 1.0000 0.0163
-12.750 -1.0412 0.03891 0.03445 -0.0566 1.0000 0.0163
-12.500 -1.0459 0.03695 0.03235 -0.0541 1.0000 0.0164
-12.250 -1.0497 0.03535 0.03063 -0.0508 1.0000 0.0165
-12.000 -1.0538 0.03399 0.02914 -0.0468 1.0000 0.0165
-11.750 -1.0539 0.03266 0.02768 -0.0432 1.0000 0.0166
-11.500 -1.0523 0.03145 0.02634 -0.0396 1.0000 0.0167
-11.250 -1.0489 0.03031 0.02508 -0.0361 1.0000 0.0168
-11.000 -1.0437 0.02921 0.02386 -0.0328 1.0000 0.0169
-10.750 -1.0365 0.02816 0.02269 -0.0297 1.0000 0.0170
-10.500 -1.0278 0.02715 0.02155 -0.0269 1.0000 0.0171
-10.250 -1.0175 0.02616 0.02044 -0.0242 1.0000 0.0172
-10.000 -0.9958 0.02503 0.01917 -0.0239 0.9989 0.0174
-9.750 -0.9724 0.02395 0.01795 -0.0238 0.9975 0.0175
-9.500 -0.9480 0.02293 0.01680 -0.0239 0.9962 0.0177
-9.250 -0.9230 0.02198 0.01572 -0.0240 0.9951 0.0179
-9.000 -0.8976 0.02109 0.01471 -0.0241 0.9941 0.0181
-8.750 -0.8740 0.02027 0.01379 -0.0237 0.9926 0.0183
-8.500 -0.8491 0.01951 0.01292 -0.0235 0.9910 0.0186
-8.250 -0.8230 0.01879 0.01211 -0.0236 0.9894 0.0188
-8.000 -0.7961 0.01812 0.01136 -0.0238 0.9880 0.0190
-7.750 -0.7685 0.01751 0.01066 -0.0240 0.9868 0.0192
-7.500 -0.7402 0.01689 0.00999 -0.0245 0.9858 0.0194
-7.250 -0.7121 0.01618 0.00925 -0.0249 0.9848 0.0198
-7.000 -0.6850 0.01567 0.00873 -0.0251 0.9834 0.0202
-6.750 -0.6599 0.01524 0.00828 -0.0247 0.9810 0.0206
-6.500 -0.6329 0.01482 0.00784 -0.0248 0.9792 0.0211
-6.250 -0.6051 0.01440 0.00739 -0.0250 0.9777 0.0216
-6.000 -0.5765 0.01399 0.00695 -0.0253 0.9764 0.0221
-5.750 -0.5466 0.01360 0.00653 -0.0259 0.9752 0.0226
-5.500 -0.5153 0.01324 0.00614 -0.0268 0.9742 0.0231
-5.250 -0.4840 0.01278 0.00568 -0.0277 0.9733 0.0239
-5.000 -0.4521 0.01242 0.00534 -0.0287 0.9725 0.0248
-4.750 -0.4294 0.01217 0.00507 -0.0276 0.9690 0.0257
-4.500 -0.4018 0.01191 0.00480 -0.0276 0.9668 0.0268
-4.250 -0.3731 0.01164 0.00453 -0.0279 0.9650 0.0282
-4.000 -0.3434 0.01136 0.00428 -0.0283 0.9635 0.0304
-3.750 -0.3124 0.01110 0.00404 -0.0290 0.9620 0.0335
-3.500 -0.2811 0.01083 0.00383 -0.0298 0.9605 0.0388
-3.250 -0.2496 0.01056 0.00363 -0.0306 0.9592 0.0495
-3.000 -0.2273 0.01037 0.00350 -0.0294 0.9541 0.0603
-2.500 -0.1699 0.00986 0.00317 -0.0297 0.9483 0.0939
-2.250 -0.1404 0.00956 0.00302 -0.0301 0.9463 0.1268
-2.000 -0.1156 0.00928 0.00291 -0.0295 0.9426 0.1665
-1.750 -0.0917 0.00893 0.00280 -0.0287 0.9379 0.2238
-1.500 -0.0650 0.00848 0.00262 -0.0285 0.9334 0.2938
-1.250 -0.0436 0.00785 0.00243 -0.0272 0.9253 0.4113
-1.000 -0.0212 0.00713 0.00221 -0.0259 0.9169 0.5465
-0.750 -0.0002 0.00669 0.00210 -0.0243 0.9060 0.6331
-0.500 0.0243 0.00637 0.00200 -0.0232 0.8949 0.6939
-0.250 0.0492 0.00608 0.00193 -0.0221 0.8826 0.7570
0.000 0.0748 0.00589 0.00191 -0.0211 0.8701 0.8145
0.250 0.1008 0.00581 0.00192 -0.0201 0.8496 0.8503
0.500 0.1275 0.00581 0.00185 -0.0193 0.8140 0.8717
0.750 0.1520 0.00597 0.00181 -0.0180 0.7535 0.8904
1.000 0.1730 0.00637 0.00186 -0.0160 0.6658 0.9058
1.250 0.1947 0.00680 0.00198 -0.0145 0.5876 0.9189
1.500 0.2164 0.00729 0.00212 -0.0130 0.4985 0.9306
1.750 0.2389 0.00784 0.00229 -0.0119 0.4021 0.9397
2.000 0.2641 0.00828 0.00244 -0.0115 0.3306 0.9457
2.250 0.2915 0.00865 0.00259 -0.0114 0.2770 0.9508
2.500 0.3162 0.00900 0.00273 -0.0108 0.2277 0.9576
2.750 0.3455 0.00943 0.00289 -0.0113 0.1746 0.9611
3.000 0.3749 0.00981 0.00306 -0.0118 0.1310 0.9652
3.250 0.4020 0.01013 0.00323 -0.0117 0.1029 0.9707
3.500 0.4329 0.01041 0.00341 -0.0124 0.0848 0.9736
3.750 0.4652 0.01067 0.00360 -0.0135 0.0722 0.9759
4.000 0.4972 0.01094 0.00380 -0.0145 0.0620 0.9784
4.250 0.5281 0.01121 0.00401 -0.0152 0.0527 0.9819
4.500 0.5592 0.01150 0.00424 -0.0160 0.0419 0.9849
4.750 0.5917 0.01184 0.00448 -0.0172 0.0329 0.9866
5.000 0.6231 0.01215 0.00476 -0.0181 0.0290 0.9887
5.250 0.6535 0.01247 0.00507 -0.0188 0.0268 0.9910
5.500 0.6831 0.01278 0.00538 -0.0193 0.0253 0.9933
5.750 0.7132 0.01312 0.00572 -0.0199 0.0240 0.9950
6.000 0.7433 0.01354 0.00613 -0.0206 0.0230 0.9966
6.250 0.7735 0.01388 0.00650 -0.0213 0.0224 0.9984
6.500 0.8035 0.01426 0.00690 -0.0219 0.0218 1.0000
6.750 0.8226 0.01460 0.00727 -0.0202 0.0214 1.0000
7.000 0.8415 0.01496 0.00765 -0.0185 0.0210 1.0000
7.250 0.8604 0.01534 0.00805 -0.0168 0.0206 1.0000
7.500 0.8791 0.01574 0.00848 -0.0150 0.0203 1.0000
7.750 0.8977 0.01617 0.00893 -0.0133 0.0200 1.0000
8.000 0.9159 0.01666 0.00944 -0.0115 0.0197 1.0000
8.250 0.9336 0.01722 0.01003 -0.0097 0.0194 1.0000
8.500 0.9504 0.01790 0.01074 -0.0077 0.0192 1.0000
8.750 0.9688 0.01843 0.01132 -0.0060 0.0190 1.0000
9.000 0.9874 0.01900 0.01194 -0.0044 0.0189 1.0000
9.250 1.0061 0.01958 0.01259 -0.0028 0.0187 1.0000
9.500 1.0250 0.02019 0.01326 -0.0013 0.0186 1.0000
9.750 1.0437 0.02083 0.01398 0.0001 0.0184 1.0000
10.000 1.0623 0.02151 0.01473 0.0016 0.0181 1.0000
10.250 1.0804 0.02225 0.01555 0.0030 0.0180 1.0000
10.500 1.0979 0.02304 0.01643 0.0046 0.0178 1.0000
10.750 1.1148 0.02388 0.01736 0.0061 0.0177 1.0000
11.000 1.1311 0.02476 0.01834 0.0077 0.0176 1.0000
11.250 1.1465 0.02570 0.01938 0.0094 0.0175 1.0000
11.500 1.1609 0.02668 0.02047 0.0112 0.0174 1.0000
11.750 1.1736 0.02769 0.02159 0.0132 0.0173 1.0000
12.000 1.1840 0.02875 0.02277 0.0155 0.0172 1.0000
12.250 1.1930 0.02989 0.02402 0.0180 0.0171 1.0000
12.500 1.2008 0.03110 0.02537 0.0203 0.0170 1.0000
12.750 1.2073 0.03243 0.02682 0.0227 0.0170 1.0000
13.000 1.2122 0.03388 0.02841 0.0250 0.0169 1.0000
13.250 1.2156 0.03547 0.03014 0.0273 0.0169 1.0000
13.500 1.2172 0.03724 0.03206 0.0294 0.0168 1.0000
13.750 1.2169 0.03924 0.03420 0.0313 0.0167 1.0000
14.000 1.2146 0.04151 0.03664 0.0328 0.0167 1.0000
14.250 1.2101 0.04414 0.03942 0.0340 0.0167 1.0000
14.500 1.2031 0.04724 0.04270 0.0345 0.0166 1.0000
14.750 1.1934 0.05099 0.04662 0.0342 0.0166 1.0000
15.000 1.1803 0.05561 0.05143 0.0328 0.0166 1.0000
15.250 1.1630 0.06155 0.05758 0.0298 0.0166 1.0000
15.500 1.1387 0.06962 0.06588 0.0245 0.0166 1.0000
15.750 1.0992 0.08224 0.07880 0.0155 0.0167 1.0000
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