S4158 (s4158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.61 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4158-il-1000000.txt Download as CSV file: xf-s4158-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S4158
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3215 0.09636 0.09411 -0.0458 0.8299 0.0119
-9.750 -0.3194 0.09210 0.08985 -0.0480 0.8286 0.0119
-9.500 -0.3171 0.08810 0.08587 -0.0500 0.8271 0.0119
-9.250 -0.3303 0.08160 0.07940 -0.0529 0.8253 0.0123
-9.000 -0.3293 0.07808 0.07588 -0.0547 0.8237 0.0124
-8.750 -0.3254 0.07549 0.07329 -0.0560 0.8220 0.0126
-8.500 -0.3273 0.07178 0.06960 -0.0580 0.8200 0.0127
-8.250 -0.3291 0.06865 0.06647 -0.0597 0.8177 0.0129
-8.000 -0.3446 0.06330 0.06117 -0.0639 0.8154 0.0128
-7.750 -0.3464 0.05771 0.05555 -0.0689 0.8131 0.0129
-7.500 -0.3436 0.05255 0.05031 -0.0724 0.8109 0.0131
-7.250 -0.3385 0.04747 0.04509 -0.0748 0.8089 0.0134
-7.000 -0.3310 0.04249 0.03993 -0.0763 0.8071 0.0138
-6.750 -0.3209 0.03766 0.03488 -0.0770 0.8054 0.0143
-6.000 -0.2893 0.01927 0.01465 -0.0737 0.8003 0.0122
-5.750 -0.2682 0.01637 0.01147 -0.0729 0.7987 0.0111
-5.500 -0.2439 0.01474 0.00959 -0.0724 0.7971 0.0110
-5.250 -0.2183 0.01360 0.00828 -0.0720 0.7955 0.0111
-5.000 -0.1918 0.01285 0.00740 -0.0717 0.7940 0.0115
-4.750 -0.1647 0.01237 0.00683 -0.0716 0.7924 0.0118
-4.500 -0.1382 0.01172 0.00608 -0.0713 0.7909 0.0121
-4.250 -0.1131 0.01083 0.00508 -0.0709 0.7890 0.0124
-4.000 -0.0863 0.01026 0.00446 -0.0707 0.7875 0.0129
-3.750 -0.0589 0.00985 0.00403 -0.0707 0.7856 0.0134
-3.500 -0.0312 0.00952 0.00367 -0.0707 0.7836 0.0139
-3.250 -0.0034 0.00926 0.00338 -0.0706 0.7815 0.0148
-3.000 0.0245 0.00901 0.00309 -0.0706 0.7795 0.0157
-2.750 0.0523 0.00873 0.00274 -0.0705 0.7775 0.0171
-2.500 0.0801 0.00850 0.00249 -0.0704 0.7754 0.0205
-2.250 0.1077 0.00818 0.00229 -0.0704 0.7732 0.0458
-2.000 0.1356 0.00792 0.00215 -0.0705 0.7706 0.0770
-1.750 0.1633 0.00766 0.00201 -0.0706 0.7676 0.1148
-1.500 0.1906 0.00732 0.00188 -0.0706 0.7647 0.1788
-1.250 0.2172 0.00691 0.00176 -0.0705 0.7620 0.2807
-1.000 0.2438 0.00656 0.00170 -0.0704 0.7593 0.3826
-0.750 0.2703 0.00617 0.00166 -0.0704 0.7564 0.4922
-0.500 0.2957 0.00575 0.00163 -0.0700 0.7532 0.6231
-0.250 0.3210 0.00541 0.00159 -0.0694 0.7502 0.7239
0.000 0.3444 0.00507 0.00157 -0.0683 0.7473 0.8355
0.250 0.3758 0.00484 0.00160 -0.0687 0.7442 0.9392
0.500 0.4259 0.00481 0.00159 -0.0735 0.7407 0.9744
0.750 0.4675 0.00481 0.00155 -0.0765 0.7369 0.9885
1.000 0.5123 0.00479 0.00149 -0.0802 0.7332 0.9967
1.250 0.5513 0.00477 0.00145 -0.0827 0.7285 1.0000
1.500 0.5778 0.00475 0.00142 -0.0824 0.7223 1.0000
1.750 0.6041 0.00475 0.00138 -0.0821 0.7146 1.0000
2.000 0.6305 0.00475 0.00134 -0.0818 0.7050 1.0000
2.250 0.6571 0.00476 0.00134 -0.0816 0.6943 1.0000
2.500 0.6835 0.00480 0.00135 -0.0814 0.6830 1.0000
2.750 0.7098 0.00487 0.00137 -0.0811 0.6700 1.0000
3.000 0.7360 0.00496 0.00141 -0.0808 0.6558 1.0000
3.250 0.7619 0.00508 0.00147 -0.0805 0.6397 1.0000
3.500 0.7877 0.00523 0.00155 -0.0802 0.6234 1.0000
3.750 0.8131 0.00540 0.00166 -0.0798 0.6055 1.0000
4.000 0.8386 0.00557 0.00177 -0.0794 0.5873 1.0000
4.250 0.8635 0.00579 0.00191 -0.0790 0.5650 1.0000
4.500 0.8872 0.00611 0.00210 -0.0784 0.5335 1.0000
4.750 0.9100 0.00647 0.00232 -0.0776 0.4966 1.0000
5.000 0.9326 0.00684 0.00254 -0.0769 0.4637 1.0000
5.250 0.9543 0.00725 0.00280 -0.0760 0.4290 1.0000
5.500 0.9764 0.00762 0.00304 -0.0751 0.4004 1.0000
5.750 0.9976 0.00803 0.00333 -0.0742 0.3683 1.0000
6.000 1.0185 0.00845 0.00361 -0.0731 0.3374 1.0000
6.250 1.0384 0.00891 0.00392 -0.0720 0.3041 1.0000
6.500 1.0566 0.00946 0.00429 -0.0706 0.2651 1.0000
6.750 1.0742 0.01003 0.00469 -0.0691 0.2308 1.0000
7.000 1.0919 0.01057 0.00508 -0.0676 0.2016 1.0000
7.250 1.1092 0.01109 0.00547 -0.0660 0.1753 1.0000
7.500 1.1269 0.01157 0.00586 -0.0645 0.1537 1.0000
7.750 1.1428 0.01211 0.00628 -0.0628 0.1323 1.0000
8.000 1.1568 0.01265 0.00673 -0.0607 0.1112 1.0000
8.250 1.1659 0.01328 0.00725 -0.0577 0.0906 1.0000
8.500 1.1765 0.01394 0.00781 -0.0552 0.0736 1.0000
8.750 1.1889 0.01459 0.00840 -0.0531 0.0607 1.0000
9.000 1.2032 0.01519 0.00896 -0.0514 0.0518 1.0000
9.250 1.2178 0.01580 0.00955 -0.0497 0.0450 1.0000
9.500 1.2329 0.01641 0.01016 -0.0482 0.0402 1.0000
9.750 1.2476 0.01706 0.01081 -0.0466 0.0356 1.0000
10.000 1.2637 0.01763 0.01141 -0.0453 0.0329 1.0000
10.250 1.2771 0.01839 0.01215 -0.0437 0.0290 1.0000
10.500 1.2923 0.01905 0.01285 -0.0424 0.0269 1.0000
10.750 1.3080 0.01968 0.01351 -0.0412 0.0249 1.0000
11.000 1.3211 0.02049 0.01433 -0.0397 0.0225 1.0000
11.250 1.3328 0.02142 0.01530 -0.0381 0.0204 1.0000
11.500 1.3483 0.02208 0.01601 -0.0369 0.0192 1.0000
11.750 1.3615 0.02293 0.01687 -0.0356 0.0175 1.0000
12.000 1.3686 0.02422 0.01820 -0.0337 0.0153 1.0000
12.250 1.3833 0.02498 0.01901 -0.0326 0.0145 1.0000
12.500 1.3953 0.02593 0.02001 -0.0313 0.0137 1.0000
12.750 1.4068 0.02694 0.02104 -0.0301 0.0124 1.0000
13.000 1.4107 0.02857 0.02274 -0.0282 0.0111 1.0000
13.250 1.4218 0.02964 0.02387 -0.0270 0.0107 1.0000
13.500 1.4317 0.03084 0.02513 -0.0258 0.0101 1.0000
13.750 1.4411 0.03209 0.02644 -0.0246 0.0097 1.0000
14.000 1.4477 0.03360 0.02803 -0.0233 0.0094 1.0000
14.250 1.4548 0.03510 0.02958 -0.0222 0.0088 1.0000
14.500 1.4588 0.03695 0.03150 -0.0210 0.0083 1.0000
14.750 1.4523 0.03986 0.03453 -0.0194 0.0079 1.0000
15.000 1.4571 0.04181 0.03657 -0.0185 0.0078 1.0000
15.250 1.4638 0.04361 0.03848 -0.0179 0.0075 1.0000
15.500 1.4667 0.04586 0.04082 -0.0172 0.0074 1.0000
15.750 1.4717 0.04795 0.04299 -0.0168 0.0071 1.0000
16.000 1.4731 0.05051 0.04565 -0.0164 0.0069 1.0000
16.250 1.4765 0.05293 0.04815 -0.0162 0.0067 1.0000
16.500 1.4720 0.05638 0.05172 -0.0161 0.0066 1.0000
16.750 1.4737 0.05917 0.05459 -0.0162 0.0063 1.0000
17.000 1.4721 0.06246 0.05797 -0.0166 0.0062 1.0000
17.250 1.4672 0.06631 0.06192 -0.0171 0.0060 1.0000
17.500 1.4575 0.07098 0.06670 -0.0181 0.0058 1.0000
17.750 1.4474 0.07589 0.07174 -0.0193 0.0058 1.0000
18.000 1.4338 0.08149 0.07748 -0.0210 0.0056 1.0000
18.250 1.4126 0.08855 0.08470 -0.0234 0.0055 1.0000
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