S4158 (s4158-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 500,000 Max Cl/Cd: 109.05 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4158-il-500000-n5.txt Download as CSV file: xf-s4158-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3280 0.08779 0.08487 -0.0487 0.8217 0.0093
-9.250 -0.3238 0.08468 0.08175 -0.0504 0.8203 0.0096
-9.000 -0.3252 0.08041 0.07749 -0.0526 0.8189 0.0095
-8.750 -0.3223 0.07726 0.07435 -0.0544 0.8172 0.0101
-8.500 -0.3296 0.07216 0.06929 -0.0572 0.8150 0.0098
-8.250 -0.3358 0.06790 0.06507 -0.0599 0.8126 0.0099
-8.000 -0.4095 0.04301 0.03988 -0.0745 0.8079 0.0084
-7.750 -0.4257 0.03283 0.02906 -0.0759 0.8056 0.0083
-7.500 -0.4203 0.02760 0.02323 -0.0755 0.8040 0.0083
-7.250 -0.4052 0.02437 0.01953 -0.0749 0.8024 0.0083
-7.000 -0.3852 0.02220 0.01699 -0.0745 0.8007 0.0084
-6.750 -0.3635 0.02039 0.01486 -0.0741 0.7989 0.0085
-6.500 -0.3425 0.01823 0.01236 -0.0735 0.7971 0.0087
-6.250 -0.3184 0.01705 0.01099 -0.0732 0.7954 0.0090
-6.000 -0.2931 0.01622 0.01002 -0.0730 0.7938 0.0093
-5.750 -0.2673 0.01548 0.00916 -0.0728 0.7923 0.0096
-5.500 -0.2413 0.01484 0.00841 -0.0726 0.7908 0.0099
-5.250 -0.2152 0.01420 0.00766 -0.0723 0.7895 0.0102
-5.000 -0.1887 0.01364 0.00700 -0.0722 0.7879 0.0106
-4.750 -0.1619 0.01311 0.00640 -0.0721 0.7860 0.0109
-4.500 -0.1348 0.01269 0.00592 -0.0720 0.7841 0.0114
-4.250 -0.1076 0.01232 0.00550 -0.0720 0.7821 0.0118
-4.000 -0.0812 0.01177 0.00489 -0.0718 0.7803 0.0125
-3.750 -0.0542 0.01137 0.00444 -0.0716 0.7784 0.0132
-3.500 -0.0269 0.01106 0.00408 -0.0715 0.7767 0.0139
-3.250 0.0006 0.01079 0.00375 -0.0715 0.7751 0.0149
-3.000 0.0284 0.01056 0.00348 -0.0715 0.7730 0.0161
-2.750 0.0562 0.01030 0.00322 -0.0715 0.7705 0.0190
-2.500 0.0839 0.01005 0.00301 -0.0715 0.7679 0.0276
-2.250 0.1114 0.00979 0.00283 -0.0715 0.7654 0.0488
-2.000 0.1390 0.00956 0.00267 -0.0715 0.7630 0.0709
-1.750 0.1665 0.00934 0.00252 -0.0715 0.7609 0.1000
-1.500 0.1937 0.00904 0.00242 -0.0715 0.7580 0.1535
-1.250 0.2203 0.00863 0.00233 -0.0716 0.7543 0.2477
-1.000 0.2468 0.00826 0.00224 -0.0715 0.7507 0.3406
-0.750 0.2736 0.00797 0.00213 -0.0714 0.7474 0.4135
-0.500 0.2997 0.00763 0.00209 -0.0712 0.7436 0.5100
-0.250 0.3251 0.00729 0.00207 -0.0708 0.7390 0.6118
0.000 0.3493 0.00694 0.00205 -0.0700 0.7351 0.7155
0.250 0.3728 0.00660 0.00203 -0.0688 0.7318 0.8183
0.500 0.4142 0.00639 0.00209 -0.0713 0.7271 0.9345
0.750 0.4656 0.00636 0.00205 -0.0763 0.7225 0.9749
1.000 0.5030 0.00636 0.00199 -0.0784 0.7182 0.9884
1.250 0.5406 0.00636 0.00199 -0.0806 0.7120 0.9968
1.500 0.5734 0.00636 0.00195 -0.0818 0.7057 1.0000
1.750 0.5997 0.00638 0.00195 -0.0815 0.6981 1.0000
2.000 0.6258 0.00640 0.00193 -0.0811 0.6897 1.0000
2.250 0.6518 0.00644 0.00192 -0.0808 0.6779 1.0000
2.500 0.6774 0.00650 0.00191 -0.0803 0.6612 1.0000
2.750 0.7026 0.00661 0.00193 -0.0798 0.6410 1.0000
3.000 0.7276 0.00676 0.00198 -0.0793 0.6218 1.0000
3.250 0.7525 0.00694 0.00207 -0.0788 0.6032 1.0000
3.500 0.7773 0.00713 0.00219 -0.0783 0.5837 1.0000
3.750 0.8015 0.00735 0.00234 -0.0777 0.5631 1.0000
4.000 0.8255 0.00759 0.00249 -0.0771 0.5410 1.0000
4.250 0.8489 0.00788 0.00268 -0.0764 0.5181 1.0000
4.500 0.8720 0.00817 0.00288 -0.0757 0.4944 1.0000
4.750 0.8947 0.00848 0.00312 -0.0749 0.4712 1.0000
5.000 0.9158 0.00889 0.00340 -0.0739 0.4401 1.0000
5.250 0.9347 0.00942 0.00373 -0.0726 0.4005 1.0000
5.500 0.9540 0.00992 0.00407 -0.0713 0.3655 1.0000
5.750 0.9723 0.01045 0.00444 -0.0699 0.3304 1.0000
6.000 0.9900 0.01101 0.00482 -0.0684 0.2925 1.0000
6.250 1.0073 0.01156 0.00522 -0.0669 0.2601 1.0000
6.500 1.0240 0.01213 0.00564 -0.0653 0.2302 1.0000
6.750 1.0402 0.01270 0.00608 -0.0636 0.2026 1.0000
7.000 1.0568 0.01321 0.00651 -0.0620 0.1809 1.0000
7.250 1.0715 0.01376 0.00697 -0.0601 0.1600 1.0000
7.500 1.0839 0.01431 0.00744 -0.0577 0.1401 1.0000
7.750 1.0963 0.01491 0.00796 -0.0555 0.1222 1.0000
8.000 1.1090 0.01556 0.00852 -0.0534 0.1043 1.0000
8.250 1.1220 0.01624 0.00914 -0.0515 0.0870 1.0000
8.500 1.1355 0.01694 0.00978 -0.0497 0.0733 1.0000
8.750 1.1498 0.01761 0.01042 -0.0481 0.0634 1.0000
9.000 1.1641 0.01831 0.01109 -0.0465 0.0553 1.0000
9.250 1.1782 0.01903 0.01180 -0.0450 0.0479 1.0000
9.500 1.1933 0.01971 0.01249 -0.0436 0.0427 1.0000
9.750 1.2069 0.02049 0.01327 -0.0421 0.0375 1.0000
10.000 1.2218 0.02120 0.01402 -0.0408 0.0339 1.0000
10.250 1.2360 0.02197 0.01481 -0.0395 0.0310 1.0000
10.500 1.2488 0.02285 0.01571 -0.0380 0.0279 1.0000
10.750 1.2632 0.02362 0.01654 -0.0368 0.0261 1.0000
11.000 1.2768 0.02446 0.01743 -0.0355 0.0241 1.0000
11.250 1.2886 0.02545 0.01845 -0.0341 0.0220 1.0000
11.500 1.3004 0.02644 0.01949 -0.0327 0.0202 1.0000
11.750 1.3129 0.02740 0.02052 -0.0315 0.0188 1.0000
12.000 1.3243 0.02846 0.02162 -0.0302 0.0173 1.0000
12.250 1.3340 0.02966 0.02286 -0.0289 0.0159 1.0000
12.500 1.3432 0.03093 0.02420 -0.0275 0.0149 1.0000
12.750 1.3535 0.03212 0.02548 -0.0264 0.0140 1.0000
13.000 1.3627 0.03342 0.02686 -0.0252 0.0131 1.0000
13.250 1.3706 0.03486 0.02838 -0.0240 0.0123 1.0000
13.500 1.3760 0.03656 0.03013 -0.0228 0.0114 1.0000
13.750 1.3826 0.03819 0.03185 -0.0217 0.0107 1.0000
14.000 1.3892 0.03989 0.03364 -0.0207 0.0102 1.0000
14.250 1.3954 0.04166 0.03551 -0.0199 0.0097 1.0000
14.500 1.4004 0.04361 0.03756 -0.0191 0.0093 1.0000
14.750 1.4043 0.04574 0.03978 -0.0184 0.0088 1.0000
15.000 1.4072 0.04806 0.04218 -0.0179 0.0085 1.0000
15.250 1.4075 0.05074 0.04496 -0.0174 0.0081 1.0000
15.500 1.4055 0.05380 0.04812 -0.0171 0.0078 1.0000
15.750 1.4080 0.05641 0.05087 -0.0170 0.0076 1.0000
16.000 1.4095 0.05921 0.05379 -0.0171 0.0073 1.0000
16.250 1.4092 0.06235 0.05705 -0.0173 0.0071 1.0000
16.500 1.4057 0.06602 0.06085 -0.0178 0.0069 1.0000
16.750 1.4038 0.06959 0.06454 -0.0184 0.0067 1.0000
17.000 1.3998 0.07353 0.06861 -0.0193 0.0066 1.0000
17.250 1.3972 0.07739 0.07259 -0.0204 0.0063 1.0000
17.500 1.3925 0.08170 0.07700 -0.0217 0.0061 1.0000
17.750 1.3831 0.08689 0.08234 -0.0235 0.0061 1.0000
18.000 1.3751 0.09197 0.08754 -0.0254 0.0059 1.0000
18.250 1.3650 0.09758 0.09327 -0.0277 0.0058 1.0000
18.500 1.3534 0.10360 0.09944 -0.0303 0.0057 1.0000
18.750 1.3417 0.10977 0.10574 -0.0331 0.0057 1.0000
19.000 1.3287 0.11632 0.11243 -0.0363 0.0056 1.0000
19.250 1.3139 0.12339 0.11963 -0.0399 0.0056 1.0000
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