S4180-098-84 (s4180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.88 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4180-il-1000000.txt Download as CSV file: xf-s4180-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S4180-098-84
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3509 0.11665 0.11496 -0.0167 1.0000 0.0136
-10.500 -0.3475 0.11261 0.11093 -0.0188 1.0000 0.0137
-10.250 -0.3425 0.10902 0.10735 -0.0204 1.0000 0.0138
-10.000 -0.3376 0.10539 0.10373 -0.0220 1.0000 0.0138
-9.750 -0.3350 0.10147 0.09982 -0.0228 1.0000 0.0140
-9.500 -0.3269 0.09903 0.09739 -0.0234 1.0000 0.0142
-9.250 -0.3192 0.09652 0.09490 -0.0242 1.0000 0.0143
-9.000 -0.3124 0.09384 0.09224 -0.0252 1.0000 0.0145
-8.750 -0.3064 0.09114 0.08956 -0.0262 1.0000 0.0147
-8.000 -0.2778 0.08101 0.07946 -0.0344 0.9715 0.0159
-7.750 -0.2572 0.07273 0.07107 -0.0469 0.9264 0.0172
-7.500 -0.2292 0.05693 0.05507 -0.0401 0.8337 0.0177
-7.250 -0.2685 0.06373 0.06187 -0.0524 0.8647 0.0177
-7.000 -0.2591 0.06087 0.05894 -0.0551 0.8473 0.0179
-6.750 -0.2476 0.05746 0.05545 -0.0586 0.8314 0.0180
-6.500 -0.2331 0.05436 0.05228 -0.0619 0.8169 0.0184
-6.250 -0.2383 0.02292 0.01940 -0.0847 0.8058 0.0175
-6.000 -0.2160 0.01879 0.01489 -0.0858 0.7954 0.0163
-5.750 -0.1903 0.01617 0.01180 -0.0863 0.7845 0.0162
-5.500 -0.1631 0.01453 0.00984 -0.0865 0.7737 0.0163
-5.250 -0.1355 0.01346 0.00853 -0.0865 0.7629 0.0165
-5.000 -0.1076 0.01269 0.00756 -0.0865 0.7515 0.0168
-4.750 -0.0795 0.01207 0.00679 -0.0864 0.7400 0.0170
-4.500 -0.0512 0.01157 0.00615 -0.0864 0.7287 0.0172
-4.250 -0.0229 0.01119 0.00564 -0.0863 0.7171 0.0173
-4.000 0.0050 0.01021 0.00452 -0.0863 0.7053 0.0176
-3.750 0.0333 0.00962 0.00385 -0.0863 0.6937 0.0180
-3.500 0.0618 0.00926 0.00341 -0.0863 0.6820 0.0185
-3.250 0.0903 0.00902 0.00311 -0.0862 0.6701 0.0193
-2.750 0.1476 0.00858 0.00254 -0.0862 0.6464 0.0207
-2.500 0.1763 0.00842 0.00231 -0.0861 0.6348 0.0213
-2.250 0.2051 0.00818 0.00198 -0.0861 0.6235 0.0224
-2.000 0.2339 0.00804 0.00179 -0.0861 0.6119 0.0239
-1.750 0.2627 0.00793 0.00164 -0.0861 0.6006 0.0257
-1.500 0.2915 0.00780 0.00149 -0.0861 0.5897 0.0318
-1.250 0.3201 0.00763 0.00140 -0.0861 0.5786 0.0627
-1.000 0.3489 0.00756 0.00136 -0.0862 0.5676 0.0784
-0.750 0.3775 0.00752 0.00132 -0.0862 0.5574 0.0938
-0.500 0.4061 0.00748 0.00129 -0.0862 0.5468 0.1150
-0.250 0.4349 0.00739 0.00127 -0.0863 0.5365 0.1476
0.000 0.4635 0.00727 0.00127 -0.0864 0.5269 0.2035
0.250 0.4921 0.00709 0.00129 -0.0866 0.5168 0.2970
0.500 0.5208 0.00681 0.00133 -0.0868 0.5074 0.4276
0.750 0.5490 0.00640 0.00142 -0.0871 0.4983 0.6309
1.000 0.5746 0.00599 0.00152 -0.0865 0.4892 0.8249
1.250 0.5981 0.00573 0.00151 -0.0850 0.4809 1.0000
1.500 0.6267 0.00585 0.00154 -0.0850 0.4716 1.0000
1.750 0.6554 0.00594 0.00158 -0.0850 0.4631 1.0000
2.000 0.6838 0.00607 0.00163 -0.0850 0.4539 1.0000
2.250 0.7124 0.00616 0.00168 -0.0850 0.4453 1.0000
2.500 0.7407 0.00629 0.00174 -0.0850 0.4366 1.0000
2.750 0.7692 0.00640 0.00180 -0.0850 0.4278 1.0000
3.000 0.7975 0.00652 0.00188 -0.0850 0.4193 1.0000
3.250 0.8257 0.00665 0.00196 -0.0850 0.4106 1.0000
3.500 0.8540 0.00677 0.00204 -0.0850 0.4025 1.0000
3.750 0.8820 0.00692 0.00214 -0.0850 0.3935 1.0000
4.000 0.9102 0.00704 0.00223 -0.0849 0.3852 1.0000
4.250 0.9381 0.00720 0.00234 -0.0849 0.3758 1.0000
4.500 0.9661 0.00734 0.00246 -0.0849 0.3661 1.0000
4.750 0.9939 0.00750 0.00258 -0.0848 0.3562 1.0000
5.000 1.0214 0.00769 0.00271 -0.0848 0.3446 1.0000
5.250 1.0489 0.00786 0.00285 -0.0847 0.3341 1.0000
5.500 1.0764 0.00804 0.00300 -0.0846 0.3228 1.0000
5.750 1.1036 0.00825 0.00316 -0.0845 0.3102 1.0000
6.000 1.1307 0.00848 0.00334 -0.0844 0.2978 1.0000
6.250 1.1575 0.00873 0.00354 -0.0843 0.2842 1.0000
6.500 1.1840 0.00902 0.00376 -0.0842 0.2682 1.0000
6.750 1.2101 0.00934 0.00400 -0.0840 0.2504 1.0000
7.000 1.2359 0.00969 0.00428 -0.0837 0.2324 1.0000
7.250 1.2612 0.01010 0.00459 -0.0835 0.2138 1.0000
7.500 1.2863 0.01051 0.00491 -0.0832 0.1947 1.0000
7.750 1.3109 0.01097 0.00527 -0.0828 0.1758 1.0000
8.000 1.3353 0.01143 0.00565 -0.0825 0.1597 1.0000
8.250 1.3596 0.01189 0.00603 -0.0821 0.1451 1.0000
8.500 1.3836 0.01236 0.00644 -0.0817 0.1311 1.0000
8.750 1.4073 0.01284 0.00686 -0.0812 0.1187 1.0000
9.000 1.4310 0.01330 0.00728 -0.0807 0.1082 1.0000
9.250 1.4541 0.01378 0.00772 -0.0802 0.0983 1.0000
9.500 1.4767 0.01431 0.00820 -0.0796 0.0894 1.0000
9.750 1.4992 0.01480 0.00867 -0.0790 0.0825 1.0000
10.000 1.5216 0.01529 0.00915 -0.0784 0.0764 1.0000
10.250 1.5433 0.01580 0.00965 -0.0777 0.0715 1.0000
10.500 1.5642 0.01636 0.01022 -0.0769 0.0667 1.0000
10.750 1.5858 0.01680 0.01069 -0.0762 0.0637 1.0000
11.000 1.6050 0.01742 0.01128 -0.0752 0.0593 1.0000
11.250 1.6242 0.01799 0.01188 -0.0741 0.0562 1.0000
11.500 1.6439 0.01847 0.01241 -0.0732 0.0540 1.0000
11.750 1.6613 0.01909 0.01304 -0.0720 0.0516 1.0000
12.000 1.6754 0.01983 0.01379 -0.0703 0.0488 1.0000
12.250 1.6867 0.02049 0.01450 -0.0681 0.0470 1.0000
12.500 1.6991 0.02107 0.01515 -0.0661 0.0459 1.0000
12.750 1.7094 0.02181 0.01593 -0.0641 0.0441 1.0000
13.000 1.7175 0.02275 0.01690 -0.0620 0.0423 1.0000
13.250 1.7231 0.02395 0.01813 -0.0599 0.0401 1.0000
13.500 1.7308 0.02509 0.01935 -0.0583 0.0389 1.0000
13.750 1.7409 0.02616 0.02049 -0.0570 0.0379 1.0000
14.000 1.7489 0.02745 0.02184 -0.0557 0.0366 1.0000
14.250 1.7549 0.02899 0.02343 -0.0546 0.0354 1.0000
14.500 1.7589 0.03080 0.02528 -0.0535 0.0340 1.0000
14.750 1.7594 0.03302 0.02756 -0.0525 0.0324 1.0000
15.000 1.7658 0.03479 0.02942 -0.0519 0.0317 1.0000
15.250 1.7708 0.03678 0.03149 -0.0514 0.0308 1.0000
15.500 1.7738 0.03905 0.03384 -0.0510 0.0298 1.0000
15.750 1.7743 0.04168 0.03652 -0.0508 0.0286 1.0000
16.000 1.7726 0.04467 0.03957 -0.0508 0.0275 1.0000
16.250 1.7681 0.04811 0.04309 -0.0511 0.0264 1.0000
16.500 1.7689 0.05099 0.04606 -0.0513 0.0258 1.0000
16.750 1.7681 0.05419 0.04936 -0.0518 0.0251 1.0000
17.000 1.7651 0.05776 0.05303 -0.0525 0.0242 1.0000
17.250 1.7606 0.06167 0.05702 -0.0535 0.0234 1.0000
17.500 1.7540 0.06598 0.06140 -0.0546 0.0226 1.0000
17.750 1.7447 0.07083 0.06633 -0.0561 0.0215 1.0000
18.000 1.7391 0.07520 0.07081 -0.0575 0.0209 1.0000
18.250 1.7333 0.07973 0.07543 -0.0591 0.0203 1.0000
18.500 1.7255 0.08461 0.08041 -0.0609 0.0193 1.0000
18.750 1.7156 0.08995 0.08584 -0.0629 0.0185 1.0000
19.000 1.7030 0.09590 0.09187 -0.0654 0.0176 1.0000
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Polar data table (+)
Polar graphs
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