SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il) Reynolds number: 500,000 Max Cl/Cd: 69.49 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1095-il-500000.txt Download as CSV file: xf-sc1095-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8809 0.13470 0.13226 0.0310 1.0000 0.0091
-15.000 -0.9024 0.12471 0.12220 0.0259 1.0000 0.0089
-14.750 -0.9361 0.11307 0.11047 0.0198 1.0000 0.0088
-14.500 -0.9687 0.10227 0.09957 0.0139 1.0000 0.0087
-14.250 -1.0028 0.09135 0.08857 0.0078 1.0000 0.0086
-14.000 -1.0386 0.07997 0.07708 0.0011 1.0000 0.0085
-13.750 -1.0740 0.06767 0.06461 -0.0071 1.0000 0.0083
-13.500 -1.1021 0.05523 0.05192 -0.0179 1.0000 0.0082
-13.250 -1.1207 0.04700 0.04344 -0.0255 1.0000 0.0082
-13.000 -1.1338 0.04193 0.03815 -0.0285 1.0000 0.0082
-12.750 -1.1427 0.03848 0.03450 -0.0288 1.0000 0.0082
-12.500 -1.1483 0.03588 0.03171 -0.0273 1.0000 0.0083
-12.250 -1.1457 0.03359 0.02922 -0.0260 1.0000 0.0083
-12.000 -1.1380 0.03153 0.02697 -0.0249 1.0000 0.0084
-11.750 -1.1270 0.02967 0.02492 -0.0239 1.0000 0.0085
-11.500 -1.1133 0.02798 0.02305 -0.0229 1.0000 0.0086
-11.250 -1.0975 0.02644 0.02135 -0.0221 1.0000 0.0087
-11.000 -1.0799 0.02505 0.01979 -0.0213 1.0000 0.0088
-10.750 -1.0604 0.02385 0.01843 -0.0206 1.0000 0.0089
-10.500 -1.0429 0.02224 0.01666 -0.0198 1.0000 0.0092
-10.250 -1.0228 0.02095 0.01526 -0.0192 1.0000 0.0096
-10.000 -1.0006 0.01995 0.01416 -0.0187 1.0000 0.0100
-9.750 -0.9774 0.01905 0.01315 -0.0183 1.0000 0.0104
-9.500 -0.9538 0.01819 0.01218 -0.0178 1.0000 0.0109
-9.250 -0.9295 0.01739 0.01125 -0.0175 1.0000 0.0114
-9.000 -0.9053 0.01652 0.01028 -0.0171 1.0000 0.0123
-8.750 -0.8805 0.01572 0.00944 -0.0167 1.0000 0.0143
-8.500 -0.8557 0.01492 0.00867 -0.0164 1.0000 0.0206
-8.250 -0.8296 0.01443 0.00821 -0.0162 1.0000 0.0285
-8.000 -0.8031 0.01406 0.00777 -0.0161 1.0000 0.0327
-7.750 -0.7766 0.01368 0.00739 -0.0159 1.0000 0.0363
-7.500 -0.7498 0.01336 0.00702 -0.0158 1.0000 0.0392
-7.250 -0.7236 0.01291 0.00659 -0.0156 1.0000 0.0430
-7.000 -0.6968 0.01260 0.00625 -0.0155 1.0000 0.0463
-6.750 -0.6705 0.01221 0.00585 -0.0153 1.0000 0.0504
-6.500 -0.6439 0.01194 0.00559 -0.0150 1.0000 0.0557
-6.250 -0.6177 0.01162 0.00530 -0.0148 1.0000 0.0620
-6.000 -0.5913 0.01150 0.00516 -0.0144 1.0000 0.0687
-5.750 -0.5662 0.01127 0.00499 -0.0140 1.0000 0.0770
-5.500 -0.5414 0.01118 0.00488 -0.0133 1.0000 0.0834
-5.250 -0.5176 0.01098 0.00471 -0.0126 1.0000 0.0896
-5.000 -0.4939 0.01088 0.00458 -0.0117 1.0000 0.0939
-4.750 -0.4711 0.01061 0.00430 -0.0108 1.0000 0.0984
-4.500 -0.4483 0.01042 0.00413 -0.0099 1.0000 0.1031
-4.250 -0.4253 0.01031 0.00400 -0.0090 1.0000 0.1071
-4.000 -0.3924 0.01009 0.00375 -0.0102 0.9980 0.1112
-3.750 -0.3543 0.00979 0.00350 -0.0124 0.9951 0.1175
-3.500 -0.3145 0.00961 0.00331 -0.0150 0.9915 0.1234
-3.250 -0.2716 0.00926 0.00303 -0.0181 0.9866 0.1339
-3.000 -0.2306 0.00898 0.00281 -0.0209 0.9817 0.1456
-2.750 -0.1966 0.00872 0.00263 -0.0221 0.9753 0.1614
-2.500 -0.1639 0.00841 0.00247 -0.0231 0.9690 0.1950
-2.250 -0.1363 0.00801 0.00235 -0.0231 0.9592 0.2610
-2.000 -0.1115 0.00756 0.00224 -0.0224 0.9477 0.3470
-1.750 -0.0873 0.00707 0.00213 -0.0216 0.9362 0.4514
-1.500 -0.0636 0.00656 0.00205 -0.0207 0.9248 0.5671
-1.250 -0.0401 0.00618 0.00202 -0.0194 0.9124 0.6628
-1.000 -0.0165 0.00595 0.00198 -0.0180 0.8965 0.7300
-0.750 0.0071 0.00581 0.00195 -0.0165 0.8765 0.7788
-0.500 0.0309 0.00573 0.00193 -0.0150 0.8560 0.8171
-0.250 0.0556 0.00570 0.00192 -0.0137 0.8360 0.8488
0.000 0.0795 0.00569 0.00192 -0.0123 0.8132 0.8778
0.250 0.1034 0.00573 0.00192 -0.0108 0.7886 0.9023
0.500 0.1270 0.00580 0.00191 -0.0094 0.7606 0.9214
0.750 0.1509 0.00589 0.00190 -0.0080 0.7264 0.9390
1.000 0.1744 0.00603 0.00188 -0.0065 0.6853 0.9603
1.250 0.2060 0.00621 0.00186 -0.0069 0.6314 0.9773
1.500 0.2465 0.00654 0.00190 -0.0094 0.5629 0.9886
1.750 0.2910 0.00696 0.00199 -0.0130 0.4874 0.9958
2.000 0.3293 0.00731 0.00207 -0.0154 0.4279 1.0000
2.250 0.3536 0.00753 0.00211 -0.0149 0.3875 1.0000
2.750 0.4021 0.00798 0.00225 -0.0138 0.3212 1.0000
3.000 0.4265 0.00822 0.00235 -0.0132 0.2902 1.0000
3.250 0.4514 0.00847 0.00246 -0.0127 0.2599 1.0000
3.500 0.4770 0.00874 0.00259 -0.0123 0.2290 1.0000
3.750 0.5030 0.00905 0.00276 -0.0121 0.2003 1.0000
4.000 0.5296 0.00935 0.00294 -0.0119 0.1788 1.0000
4.250 0.5564 0.00965 0.00315 -0.0118 0.1630 1.0000
4.500 0.5835 0.00994 0.00338 -0.0117 0.1503 1.0000
4.750 0.6106 0.01023 0.00363 -0.0116 0.1401 1.0000
5.000 0.6376 0.01055 0.00389 -0.0116 0.1312 1.0000
5.250 0.6650 0.01081 0.00417 -0.0115 0.1246 1.0000
5.500 0.6920 0.01114 0.00445 -0.0114 0.1181 1.0000
5.750 0.7190 0.01149 0.00480 -0.0113 0.1130 1.0000
6.000 0.7463 0.01175 0.00509 -0.0112 0.1087 1.0000
6.250 0.7730 0.01213 0.00544 -0.0111 0.1040 1.0000
6.500 0.7993 0.01256 0.00589 -0.0109 0.1003 1.0000
6.750 0.8264 0.01285 0.00623 -0.0108 0.0976 1.0000
7.000 0.8532 0.01318 0.00661 -0.0107 0.0947 1.0000
7.250 0.8795 0.01358 0.00700 -0.0105 0.0915 1.0000
7.500 0.9047 0.01418 0.00760 -0.0102 0.0877 1.0000
7.750 0.9321 0.01432 0.00782 -0.0102 0.0849 1.0000
8.000 0.9589 0.01456 0.00810 -0.0101 0.0817 1.0000
8.250 0.9849 0.01492 0.00845 -0.0100 0.0781 1.0000
8.500 1.0100 0.01544 0.00901 -0.0097 0.0749 1.0000
8.750 1.0371 0.01558 0.00923 -0.0096 0.0722 1.0000
9.000 1.0638 0.01577 0.00945 -0.0096 0.0687 1.0000
9.250 1.0887 0.01622 0.00989 -0.0093 0.0646 1.0000
9.500 1.1155 0.01639 0.01014 -0.0092 0.0615 1.0000
9.750 1.1422 0.01654 0.01033 -0.0092 0.0568 1.0000
10.000 1.1682 0.01681 0.01061 -0.0091 0.0502 1.0000
10.250 1.1894 0.01783 0.01136 -0.0085 0.0236 1.0000
10.500 1.2081 0.01922 0.01275 -0.0076 0.0157 1.0000
10.750 1.2277 0.02041 0.01403 -0.0067 0.0137 1.0000
11.000 1.2484 0.02132 0.01508 -0.0059 0.0128 1.0000
11.250 1.2677 0.02237 0.01624 -0.0051 0.0120 1.0000
11.500 1.2849 0.02359 0.01758 -0.0041 0.0114 1.0000
11.750 1.2978 0.02519 0.01932 -0.0027 0.0109 1.0000
12.000 1.3092 0.02677 0.02106 -0.0011 0.0105 1.0000
12.250 1.3226 0.02802 0.02244 0.0002 0.0103 1.0000
12.500 1.3334 0.02940 0.02396 0.0017 0.0100 1.0000
12.750 1.3390 0.03088 0.02557 0.0037 0.0097 1.0000
13.000 1.3409 0.03258 0.02739 0.0059 0.0095 1.0000
13.250 1.3407 0.03462 0.02957 0.0074 0.0093 1.0000
13.500 1.3382 0.03712 0.03222 0.0083 0.0091 1.0000
13.750 1.3333 0.04024 0.03548 0.0083 0.0090 1.0000
14.000 1.3262 0.04411 0.03950 0.0071 0.0090 1.0000
14.250 1.3165 0.04896 0.04452 0.0047 0.0089 1.0000
14.500 1.3039 0.05501 0.05075 0.0008 0.0089 1.0000
14.750 1.2877 0.06228 0.05820 -0.0040 0.0089 1.0000
15.000 1.2679 0.07040 0.06650 -0.0092 0.0089 1.0000
15.250 1.2450 0.07890 0.07516 -0.0140 0.0090 1.0000
15.500 1.2208 0.08740 0.08380 -0.0185 0.0090 1.0000
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Polar data table (+)
Polar graphs
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