SIKORSKY SC2110 AIRFOIL (sc2110-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SIKORSKY SC2110 AIRFOIL (sc2110-il) Reynolds number: 100,000 Max Cl/Cd: 38.86 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc2110-il-100000-n5.txt Download as CSV file: xf-sc2110-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC2110 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5009 0.09240 0.08781 -0.0114 1.0000 0.0554
-8.250 -0.5010 0.08744 0.08289 -0.0166 1.0000 0.0565
-8.000 -0.5057 0.08230 0.07774 -0.0228 1.0000 0.0575
-7.750 -0.5229 0.07808 0.07318 -0.0307 1.0000 0.0601
-7.500 -0.5263 0.07509 0.06990 -0.0318 1.0000 0.0604
-7.250 -0.5180 0.06939 0.06435 -0.0317 1.0000 0.0612
-7.000 -0.5116 0.06586 0.06086 -0.0307 1.0000 0.0619
-6.750 -0.5098 0.06306 0.05804 -0.0289 1.0000 0.0627
-6.500 -0.5145 0.05461 0.04885 -0.0260 1.0000 0.0327
-6.250 -0.5079 0.05236 0.04663 -0.0241 1.0000 0.0317
-6.000 -0.4969 0.04935 0.04348 -0.0234 0.9981 0.0308
-5.750 -0.4739 0.04536 0.03917 -0.0248 0.9939 0.0295
-5.500 -0.4498 0.04107 0.03442 -0.0256 0.9894 0.0280
-5.250 -0.4223 0.03768 0.03060 -0.0266 0.9860 0.0279
-5.000 -0.3955 0.03533 0.02794 -0.0274 0.9824 0.0290
-4.750 -0.3667 0.03285 0.02506 -0.0281 0.9788 0.0299
-4.500 -0.3353 0.03037 0.02213 -0.0290 0.9760 0.0300
-4.250 -0.3050 0.02824 0.01963 -0.0295 0.9728 0.0300
-4.000 -0.2748 0.02643 0.01748 -0.0298 0.9693 0.0302
-3.750 -0.2423 0.02482 0.01557 -0.0305 0.9664 0.0307
-3.500 -0.2086 0.02349 0.01398 -0.0313 0.9639 0.0319
-3.250 -0.1811 0.02242 0.01288 -0.0314 0.9597 0.0341
-3.000 -0.1512 0.02153 0.01197 -0.0318 0.9558 0.0363
-2.750 -0.1194 0.02061 0.01099 -0.0325 0.9527 0.0379
-2.500 -0.0910 0.01990 0.01025 -0.0325 0.9485 0.0400
-2.250 -0.0645 0.01921 0.00966 -0.0325 0.9434 0.0444
-2.000 -0.0300 0.01867 0.00902 -0.0336 0.9380 0.0490
-1.750 -0.0023 0.01812 0.00848 -0.0334 0.9274 0.0562
-1.500 0.0268 0.01760 0.00797 -0.0331 0.9159 0.0705
-1.250 0.0484 0.01539 0.00742 -0.0325 0.9057 0.4555
-1.000 0.0553 0.01466 0.00803 -0.0252 0.8954 0.8195
-0.750 0.0731 0.01492 0.00838 -0.0200 0.8844 0.9133
-0.500 0.1322 0.01495 0.00823 -0.0232 0.8754 0.9650
-0.250 0.1630 0.01468 0.00782 -0.0232 0.8618 0.9728
0.000 0.1983 0.01439 0.00741 -0.0243 0.8467 0.9782
0.250 0.2314 0.01415 0.00707 -0.0250 0.8318 0.9852
0.500 0.2658 0.01389 0.00672 -0.0260 0.8155 0.9914
0.750 0.2998 0.01365 0.00641 -0.0270 0.7958 0.9979
1.000 0.3238 0.01346 0.00616 -0.0261 0.7719 1.0000
1.250 0.3436 0.01329 0.00591 -0.0243 0.7432 1.0000
1.500 0.3630 0.01312 0.00561 -0.0222 0.7022 1.0000
1.750 0.3808 0.01298 0.00516 -0.0195 0.6315 1.0000
2.000 0.3977 0.01323 0.00478 -0.0167 0.5206 1.0000
2.250 0.4168 0.01388 0.00480 -0.0152 0.4252 1.0000
2.500 0.4375 0.01443 0.00497 -0.0142 0.3747 1.0000
2.750 0.4592 0.01488 0.00516 -0.0134 0.3429 1.0000
3.000 0.4817 0.01526 0.00537 -0.0126 0.3187 1.0000
3.250 0.5047 0.01565 0.00559 -0.0120 0.2992 1.0000
3.500 0.5283 0.01603 0.00584 -0.0114 0.2829 1.0000
3.750 0.5525 0.01640 0.00611 -0.0110 0.2685 1.0000
4.000 0.5770 0.01678 0.00640 -0.0106 0.2556 1.0000
4.250 0.6016 0.01720 0.00672 -0.0102 0.2445 1.0000
4.500 0.6265 0.01761 0.00706 -0.0099 0.2341 1.0000
4.750 0.6518 0.01801 0.00743 -0.0097 0.2242 1.0000
5.000 0.6766 0.01848 0.00779 -0.0094 0.2157 1.0000
5.250 0.7022 0.01890 0.00825 -0.0092 0.2070 1.0000
5.500 0.7272 0.01941 0.00868 -0.0090 0.2001 1.0000
5.750 0.7528 0.01987 0.00917 -0.0088 0.1923 1.0000
6.250 0.8032 0.02091 0.01023 -0.0084 0.1792 1.0000
6.500 0.8282 0.02145 0.01077 -0.0082 0.1736 1.0000
6.750 0.8532 0.02206 0.01139 -0.0081 0.1682 1.0000
7.000 0.8783 0.02263 0.01205 -0.0079 0.1622 1.0000
7.250 0.9028 0.02323 0.01263 -0.0077 0.1575 1.0000
7.500 0.9276 0.02393 0.01342 -0.0075 0.1529 1.0000
7.750 0.9522 0.02460 0.01422 -0.0073 0.1480 1.0000
8.000 0.9763 0.02526 0.01489 -0.0070 0.1438 1.0000
8.250 1.0002 0.02604 0.01575 -0.0068 0.1397 1.0000
8.500 1.0240 0.02683 0.01674 -0.0065 0.1354 1.0000
8.750 1.0475 0.02763 0.01762 -0.0063 0.1318 1.0000
9.000 1.0706 0.02842 0.01841 -0.0060 0.1286 1.0000
9.250 1.0929 0.02942 0.01964 -0.0056 0.1250 1.0000
9.500 1.1147 0.03038 0.02081 -0.0052 0.1211 1.0000
9.750 1.1364 0.03129 0.02183 -0.0048 0.1179 1.0000
10.000 1.1581 0.03222 0.02278 -0.0044 0.1155 1.0000
10.250 1.1780 0.03347 0.02426 -0.0039 0.1127 1.0000
10.500 1.1959 0.03481 0.02592 -0.0032 0.1093 1.0000
10.750 1.2139 0.03597 0.02728 -0.0025 0.1063 1.0000
11.000 1.2323 0.03705 0.02845 -0.0019 0.1039 1.0000
11.250 1.2514 0.03815 0.02960 -0.0014 0.1019 1.0000
11.500 1.2634 0.03999 0.03177 -0.0003 0.0996 1.0000
11.750 1.2719 0.04195 0.03411 0.0010 0.0970 1.0000
12.000 1.2804 0.04370 0.03612 0.0023 0.0946 1.0000
12.250 1.2897 0.04524 0.03784 0.0034 0.0926 1.0000
12.500 1.2998 0.04661 0.03933 0.0046 0.0910 1.0000
12.750 1.3125 0.04784 0.04056 0.0056 0.0894 1.0000
13.000 1.3019 0.05075 0.04382 0.0077 0.0880 1.0000
13.250 1.2840 0.05445 0.04790 0.0093 0.0868 1.0000
13.500 1.2620 0.05891 0.05269 0.0099 0.0857 1.0000
13.750 1.2330 0.06472 0.05881 0.0089 0.0848 1.0000
14.000 1.1807 0.07487 0.06928 0.0041 0.0847 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SIKORSKY SC2110 AIRFOIL (sc2110-il)