SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il) Reynolds number: 100,000 Max Cl/Cd: 36.38 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1095-il-100000-n5.txt Download as CSV file: xf-sc1095-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1095 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8565 0.06960 0.06464 -0.0144 1.0000 0.0244
-11.250 -0.8798 0.06043 0.05532 -0.0229 1.0000 0.0239
-11.000 -0.9036 0.05394 0.04859 -0.0269 1.0000 0.0237
-10.750 -0.9242 0.04874 0.04302 -0.0273 1.0000 0.0239
-10.500 -0.9309 0.04457 0.03849 -0.0270 1.0000 0.0249
-10.250 -0.9208 0.04294 0.03682 -0.0265 1.0000 0.0264
-10.000 -0.9150 0.03990 0.03340 -0.0258 1.0000 0.0285
-9.750 -0.9083 0.03626 0.02923 -0.0249 1.0000 0.0313
-9.500 -0.8909 0.03519 0.02813 -0.0244 1.0000 0.0341
-9.250 -0.8750 0.03301 0.02548 -0.0237 1.0000 0.0386
-9.000 -0.8522 0.03341 0.02603 -0.0236 1.0000 0.0432
-8.750 -0.8323 0.03250 0.02484 -0.0231 1.0000 0.0489
-8.500 -0.8098 0.03229 0.02457 -0.0228 1.0000 0.0532
-8.250 -0.7901 0.03021 0.02191 -0.0220 1.0000 0.0575
-8.000 -0.7679 0.02917 0.02088 -0.0216 1.0000 0.0602
-7.750 -0.7450 0.02812 0.01968 -0.0211 1.0000 0.0634
-7.500 -0.7219 0.02676 0.01796 -0.0205 1.0000 0.0678
-7.250 -0.6985 0.02553 0.01660 -0.0200 1.0000 0.0711
-7.000 -0.6745 0.02462 0.01560 -0.0196 1.0000 0.0747
-6.750 -0.6501 0.02367 0.01440 -0.0190 1.0000 0.0802
-6.500 -0.6260 0.02277 0.01345 -0.0186 1.0000 0.0850
-6.250 -0.6015 0.02199 0.01258 -0.0181 1.0000 0.0906
-6.000 -0.5768 0.02115 0.01155 -0.0175 1.0000 0.0964
-5.750 -0.5527 0.02052 0.01094 -0.0170 1.0000 0.1029
-5.500 -0.5280 0.01991 0.01018 -0.0164 1.0000 0.1101
-5.250 -0.5042 0.01929 0.00960 -0.0158 1.0000 0.1165
-5.000 -0.4799 0.01880 0.00898 -0.0152 1.0000 0.1244
-4.750 -0.4566 0.01825 0.00851 -0.0145 1.0000 0.1324
-4.500 -0.4330 0.01776 0.00797 -0.0138 1.0000 0.1402
-4.250 -0.4100 0.01727 0.00753 -0.0130 1.0000 0.1479
-4.000 -0.3870 0.01681 0.00705 -0.0121 1.0000 0.1554
-3.750 -0.3641 0.01636 0.00664 -0.0112 1.0000 0.1632
-3.500 -0.3413 0.01594 0.00627 -0.0104 1.0000 0.1730
-3.250 -0.3184 0.01556 0.00594 -0.0096 1.0000 0.1864
-3.000 -0.2956 0.01517 0.00566 -0.0088 1.0000 0.2041
-2.750 -0.2726 0.01479 0.00541 -0.0081 1.0000 0.2300
-2.500 -0.2497 0.01436 0.00521 -0.0075 1.0000 0.2727
-2.250 -0.2269 0.01384 0.00506 -0.0070 1.0000 0.3470
-2.000 -0.2045 0.01325 0.00500 -0.0063 1.0000 0.4588
-1.750 -0.1813 0.01273 0.00507 -0.0054 0.9988 0.5900
-1.500 -0.1441 0.01243 0.00521 -0.0065 0.9887 0.7161
-1.250 -0.1038 0.01236 0.00536 -0.0080 0.9773 0.8028
-1.000 -0.0617 0.01238 0.00545 -0.0099 0.9662 0.8603
-0.750 -0.0212 0.01242 0.00549 -0.0116 0.9543 0.9042
-0.500 0.0261 0.01246 0.00554 -0.0146 0.9442 0.9504
-0.250 0.0882 0.01243 0.00548 -0.0210 0.9344 0.9849
0.000 0.1438 0.01232 0.00534 -0.0264 0.9198 1.0000
0.250 0.1730 0.01223 0.00520 -0.0265 0.8978 1.0000
0.500 0.1992 0.01212 0.00503 -0.0258 0.8704 1.0000
0.750 0.2223 0.01204 0.00486 -0.0243 0.8367 1.0000
1.000 0.2443 0.01198 0.00470 -0.0225 0.7989 1.0000
1.250 0.2663 0.01198 0.00456 -0.0208 0.7586 1.0000
1.500 0.2886 0.01202 0.00445 -0.0191 0.7146 1.0000
1.750 0.3110 0.01214 0.00436 -0.0175 0.6632 1.0000
2.000 0.3334 0.01235 0.00431 -0.0161 0.6059 1.0000
2.250 0.3559 0.01265 0.00432 -0.0147 0.5464 1.0000
2.500 0.3787 0.01303 0.00438 -0.0136 0.4891 1.0000
2.750 0.4021 0.01342 0.00451 -0.0127 0.4383 1.0000
3.000 0.4258 0.01385 0.00470 -0.0120 0.3928 1.0000
3.250 0.4498 0.01428 0.00492 -0.0113 0.3535 1.0000
3.500 0.4743 0.01470 0.00517 -0.0108 0.3179 1.0000
3.750 0.4989 0.01513 0.00547 -0.0103 0.2856 1.0000
4.000 0.5237 0.01558 0.00578 -0.0099 0.2567 1.0000
4.250 0.5485 0.01606 0.00611 -0.0095 0.2313 1.0000
4.500 0.5736 0.01652 0.00651 -0.0091 0.2102 1.0000
4.750 0.5986 0.01702 0.00693 -0.0087 0.1945 1.0000
5.000 0.6235 0.01755 0.00740 -0.0083 0.1814 1.0000
5.250 0.6483 0.01811 0.00791 -0.0078 0.1703 1.0000
5.500 0.6731 0.01867 0.00845 -0.0075 0.1603 1.0000
5.750 0.6980 0.01926 0.00906 -0.0070 0.1523 1.0000
6.000 0.7227 0.01990 0.00968 -0.0066 0.1458 1.0000
6.250 0.7475 0.02058 0.01041 -0.0062 0.1401 1.0000
6.500 0.7724 0.02123 0.01111 -0.0058 0.1342 1.0000
6.750 0.7965 0.02199 0.01182 -0.0054 0.1293 1.0000
7.000 0.8216 0.02268 0.01267 -0.0050 0.1244 1.0000
7.250 0.8463 0.02346 0.01355 -0.0046 0.1204 1.0000
7.500 0.8707 0.02429 0.01441 -0.0042 0.1171 1.0000
7.750 0.8949 0.02526 0.01544 -0.0038 0.1142 1.0000
8.000 0.9193 0.02618 0.01659 -0.0034 0.1105 1.0000
8.250 0.9431 0.02707 0.01766 -0.0029 0.1069 1.0000
8.500 0.9666 0.02800 0.01866 -0.0025 0.1039 1.0000
8.750 0.9902 0.02918 0.01985 -0.0022 0.1017 1.0000
9.000 1.0125 0.03047 0.02148 -0.0016 0.0991 1.0000
9.250 1.0338 0.03174 0.02307 -0.0009 0.0959 1.0000
9.500 1.0549 0.03288 0.02444 -0.0003 0.0927 1.0000
9.750 1.0763 0.03395 0.02561 0.0002 0.0901 1.0000
10.000 1.0954 0.03520 0.02704 0.0009 0.0867 1.0000
10.250 1.1118 0.03589 0.02810 0.0018 0.0806 1.0000
10.500 1.1306 0.03566 0.02781 0.0025 0.0746 1.0000
10.750 1.1462 0.03619 0.02872 0.0034 0.0676 1.0000
11.000 1.1622 0.03661 0.02922 0.0043 0.0627 1.0000
11.250 1.1759 0.03774 0.03072 0.0052 0.0566 1.0000
11.500 1.1884 0.03869 0.03183 0.0063 0.0512 1.0000
11.750 1.1986 0.03992 0.03328 0.0073 0.0446 1.0000
12.000 1.2022 0.04183 0.03541 0.0088 0.0386 1.0000
12.250 1.2006 0.04385 0.03749 0.0102 0.0349 1.0000
12.500 1.1936 0.04693 0.04082 0.0111 0.0318 1.0000
12.750 1.1833 0.05063 0.04469 0.0107 0.0301 1.0000
13.000 1.1683 0.05552 0.04976 0.0087 0.0293 1.0000
13.250 1.1479 0.06220 0.05667 0.0045 0.0291 1.0000
13.500 1.1187 0.07175 0.06654 -0.0022 0.0298 1.0000
13.750 1.0720 0.08566 0.08079 -0.0113 0.0328 1.0000
14.000 1.0336 0.09779 0.09302 -0.0184 0.0352 1.0000
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Polar data table (+)
Polar graphs
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