NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 500,000 Max Cl/Cd: 85.61 at α=-1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21010-il-500000-n5.txt Download as CSV file: xf-sc21010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1010 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8409 0.08011 0.07703 -0.0528 0.9999 0.0145
-16.750 -0.8881 0.06657 0.06327 -0.0616 0.9999 0.0144
-16.500 -0.9158 0.05758 0.05409 -0.0679 0.9999 0.0144
-16.250 -0.9350 0.05085 0.04720 -0.0726 0.9999 0.0144
-16.000 -0.9499 0.04559 0.04178 -0.0758 0.9999 0.0144
-15.750 -0.9634 0.04152 0.03757 -0.0773 0.9999 0.0145
-15.500 -0.9789 0.03840 0.03433 -0.0768 0.9999 0.0145
-15.250 -0.9993 0.03607 0.03192 -0.0741 0.9999 0.0146
-15.000 -1.0052 0.03360 0.02930 -0.0740 0.9999 0.0147
-14.750 -0.9817 0.03069 0.02616 -0.0796 0.9977 0.0149
-14.500 -0.9543 0.02840 0.02364 -0.0843 0.9958 0.0151
-14.250 -0.9260 0.02654 0.02158 -0.0880 0.9945 0.0153
-14.000 -0.8984 0.02479 0.01970 -0.0911 0.9930 0.0157
-13.750 -0.8703 0.02356 0.01837 -0.0934 0.9913 0.0160
-13.500 -0.8408 0.02258 0.01730 -0.0956 0.9898 0.0164
-13.250 -0.8103 0.02169 0.01632 -0.0977 0.9883 0.0169
-13.000 -0.7791 0.02079 0.01531 -0.0999 0.9871 0.0174
-12.750 -0.7473 0.01987 0.01427 -0.1021 0.9860 0.0179
-12.500 -0.7151 0.01899 0.01327 -0.1042 0.9851 0.0183
-12.250 -0.6826 0.01820 0.01236 -0.1063 0.9843 0.0188
-12.000 -0.6493 0.01730 0.01138 -0.1087 0.9836 0.0193
-11.750 -0.6180 0.01663 0.01067 -0.1104 0.9821 0.0200
-11.500 -0.5873 0.01607 0.01007 -0.1118 0.9800 0.0206
-11.250 -0.5551 0.01552 0.00946 -0.1135 0.9784 0.0215
-11.000 -0.5223 0.01501 0.00888 -0.1152 0.9770 0.0224
-10.750 -0.4888 0.01448 0.00829 -0.1171 0.9759 0.0234
-10.500 -0.4548 0.01396 0.00775 -0.1191 0.9749 0.0246
-10.250 -0.4209 0.01354 0.00729 -0.1209 0.9739 0.0259
-10.000 -0.3870 0.01313 0.00684 -0.1227 0.9730 0.0272
-9.750 -0.3527 0.01269 0.00636 -0.1246 0.9721 0.0286
-9.500 -0.3184 0.01229 0.00595 -0.1265 0.9712 0.0304
-9.250 -0.2877 0.01199 0.00563 -0.1274 0.9686 0.0324
-9.000 -0.2563 0.01168 0.00529 -0.1286 0.9661 0.0345
-8.750 -0.2236 0.01134 0.00495 -0.1300 0.9642 0.0371
-8.500 -0.1907 0.01106 0.00465 -0.1314 0.9624 0.0397
-8.250 -0.1575 0.01076 0.00435 -0.1328 0.9608 0.0432
-8.000 -0.1242 0.01049 0.00409 -0.1343 0.9593 0.0476
-7.750 -0.0906 0.01021 0.00384 -0.1358 0.9580 0.0538
-7.500 -0.0588 0.00998 0.00363 -0.1369 0.9556 0.0616
-7.250 -0.0283 0.00976 0.00345 -0.1377 0.9521 0.0716
-7.000 0.0036 0.00951 0.00327 -0.1388 0.9492 0.0870
-6.750 0.0360 0.00927 0.00309 -0.1400 0.9465 0.1050
-6.500 0.0687 0.00903 0.00292 -0.1412 0.9443 0.1264
-6.000 0.1333 0.00846 0.00264 -0.1437 0.9385 0.2023
-5.750 0.1660 0.00813 0.00252 -0.1451 0.9355 0.2610
-5.500 0.1990 0.00782 0.00243 -0.1465 0.9327 0.3249
-5.250 0.2318 0.00758 0.00237 -0.1478 0.9301 0.3815
-5.000 0.2638 0.00743 0.00232 -0.1488 0.9277 0.4221
-4.750 0.2939 0.00735 0.00234 -0.1493 0.9237 0.4493
-4.500 0.3243 0.00727 0.00235 -0.1498 0.9199 0.4779
-4.250 0.3546 0.00722 0.00235 -0.1503 0.9165 0.4974
-4.000 0.3852 0.00718 0.00234 -0.1508 0.9135 0.5145
-3.750 0.4151 0.00714 0.00238 -0.1512 0.9096 0.5342
-3.500 0.4446 0.00712 0.00242 -0.1514 0.9046 0.5543
-3.250 0.4742 0.00707 0.00238 -0.1515 0.8975 0.5699
-3.000 0.5022 0.00703 0.00235 -0.1512 0.8834 0.5803
-2.750 0.5298 0.00702 0.00231 -0.1507 0.8646 0.5900
-2.500 0.5577 0.00702 0.00229 -0.1504 0.8449 0.6012
-2.250 0.5855 0.00707 0.00229 -0.1501 0.8219 0.6114
-2.000 0.6125 0.00718 0.00230 -0.1495 0.7860 0.6218
-1.750 0.6378 0.00745 0.00234 -0.1486 0.7242 0.6319
-1.500 0.6561 0.00845 0.00259 -0.1464 0.5610 0.6419
-1.250 0.6768 0.00945 0.00299 -0.1452 0.4249 0.6517
-1.000 0.6997 0.01026 0.00333 -0.1443 0.3153 0.6605
-0.750 0.7236 0.01096 0.00365 -0.1437 0.2268 0.6695
-0.500 0.7483 0.01153 0.00395 -0.1432 0.1604 0.6778
-0.250 0.7740 0.01199 0.00422 -0.1427 0.1187 0.6865
0.000 0.8000 0.01237 0.00449 -0.1423 0.0901 0.6938
0.250 0.8265 0.01269 0.00475 -0.1420 0.0738 0.7010
0.500 0.8530 0.01301 0.00500 -0.1416 0.0605 0.7075
0.750 0.8793 0.01332 0.00528 -0.1412 0.0517 0.7135
1.000 0.9056 0.01364 0.00558 -0.1408 0.0459 0.7199
1.250 0.9319 0.01393 0.00588 -0.1404 0.0419 0.7260
1.500 0.9577 0.01427 0.00622 -0.1399 0.0384 0.7329
1.750 0.9839 0.01456 0.00654 -0.1394 0.0361 0.7397
2.000 1.0095 0.01489 0.00690 -0.1389 0.0336 0.7457
2.250 1.0349 0.01528 0.00729 -0.1383 0.0315 0.7517
2.500 1.0606 0.01560 0.00764 -0.1378 0.0297 0.7568
2.750 1.0858 0.01596 0.00804 -0.1371 0.0281 0.7617
3.000 1.1104 0.01640 0.00848 -0.1364 0.0266 0.7673
3.250 1.1351 0.01682 0.00895 -0.1356 0.0255 0.7728
3.500 1.1595 0.01722 0.00940 -0.1349 0.0243 0.7784
3.750 1.1840 0.01763 0.00986 -0.1341 0.0232 0.7849
4.000 1.2077 0.01809 0.01033 -0.1332 0.0221 0.7904
4.250 1.2308 0.01863 0.01091 -0.1322 0.0211 0.7959
4.500 1.2544 0.01911 0.01146 -0.1313 0.0204 0.8011
4.750 1.2774 0.01962 0.01204 -0.1303 0.0197 0.8053
5.000 1.3001 0.02015 0.01262 -0.1292 0.0190 0.8099
5.250 1.3226 0.02069 0.01321 -0.1282 0.0184 0.8148
5.500 1.3444 0.02131 0.01387 -0.1270 0.0179 0.8192
5.750 1.3643 0.02211 0.01472 -0.1255 0.0174 0.8240
6.000 1.3854 0.02277 0.01548 -0.1242 0.0170 0.8296
6.250 1.4059 0.02347 0.01627 -0.1228 0.0167 0.8345
6.500 1.4259 0.02417 0.01708 -0.1213 0.0162 0.8391
6.750 1.4457 0.02487 0.01787 -0.1198 0.0158 0.8440
7.000 1.4653 0.02556 0.01863 -0.1183 0.0154 0.8487
7.250 1.4838 0.02627 0.01943 -0.1167 0.0150 0.8531
7.500 1.5015 0.02703 0.02026 -0.1149 0.0147 0.8579
7.750 1.5177 0.02789 0.02121 -0.1129 0.0145 0.8628
8.000 1.5315 0.02886 0.02228 -0.1106 0.0142 0.8679
8.250 1.5424 0.03010 0.02361 -0.1078 0.0139 0.8738
8.500 1.5539 0.03109 0.02476 -0.1050 0.0138 0.8799
8.750 1.5632 0.03216 0.02599 -0.1020 0.0137 0.8872
9.000 1.5723 0.03334 0.02735 -0.0991 0.0135 0.8950
9.250 1.5804 0.03461 0.02879 -0.0961 0.0133 0.9039
9.500 1.5868 0.03596 0.03032 -0.0930 0.0131 0.9154
10.000 1.5939 0.03893 0.03364 -0.0864 0.0128 1.0001
10.250 1.5974 0.04074 0.03561 -0.0836 0.0127 1.0001
10.500 1.5997 0.04270 0.03773 -0.0809 0.0126 1.0001
10.750 1.6004 0.04482 0.04001 -0.0783 0.0124 1.0001
11.000 1.6001 0.04708 0.04243 -0.0758 0.0123 1.0001
11.250 1.5986 0.04952 0.04502 -0.0736 0.0122 1.0001
11.500 1.5952 0.05223 0.04789 -0.0716 0.0121 1.0001
11.750 1.5914 0.05510 0.05091 -0.0699 0.0119 1.0001
12.000 1.5850 0.05841 0.05437 -0.0686 0.0118 1.0001
12.250 1.5764 0.06216 0.05828 -0.0677 0.0118 1.0001
12.500 1.5665 0.06633 0.06261 -0.0674 0.0117 1.0001
12.750 1.5551 0.07099 0.06743 -0.0678 0.0116 1.0001
13.000 1.5386 0.07687 0.07349 -0.0692 0.0116 1.0001
13.250 1.5201 0.08379 0.08061 -0.0720 0.0115 1.0001
13.500 1.4919 0.09352 0.09059 -0.0773 0.0115 1.0001
13.750 1.4522 0.10717 0.10454 -0.0861 0.0116 1.0001
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