BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.54 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b540ols-il-1000000-n5.txt Download as CSV file: xf-b540ols-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BELL 540 AIRFOIL (MODIFIED NACA 0012)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.3645 0.08939 0.08635 0.0175 1.0000 0.0119
-17.000 -1.4147 0.07730 0.07407 0.0109 1.0000 0.0118
-16.750 -1.4609 0.06600 0.06258 0.0045 1.0000 0.0117
-16.500 -1.4971 0.05606 0.05245 -0.0017 1.0000 0.0117
-16.250 -1.5205 0.04755 0.04375 -0.0080 1.0000 0.0117
-16.000 -1.5327 0.04088 0.03689 -0.0138 1.0000 0.0118
-15.750 -1.5391 0.03634 0.03220 -0.0172 1.0000 0.0118
-15.500 -1.5424 0.03338 0.02911 -0.0179 1.0000 0.0119
-15.250 -1.5429 0.03138 0.02700 -0.0167 1.0000 0.0121
-15.000 -1.5386 0.02989 0.02541 -0.0150 1.0000 0.0122
-14.750 -1.5278 0.02857 0.02399 -0.0139 1.0000 0.0123
-14.500 -1.5142 0.02739 0.02271 -0.0129 1.0000 0.0125
-14.250 -1.4988 0.02630 0.02154 -0.0120 1.0000 0.0126
-14.000 -1.4818 0.02530 0.02044 -0.0112 1.0000 0.0128
-13.750 -1.4636 0.02436 0.01943 -0.0105 1.0000 0.0130
-13.500 -1.4443 0.02349 0.01847 -0.0098 1.0000 0.0132
-13.250 -1.4240 0.02268 0.01757 -0.0091 1.0000 0.0133
-13.000 -1.4029 0.02193 0.01674 -0.0085 1.0000 0.0135
-12.750 -1.3820 0.02109 0.01582 -0.0079 1.0000 0.0137
-12.500 -1.3605 0.02027 0.01494 -0.0074 1.0000 0.0141
-12.250 -1.3379 0.01958 0.01420 -0.0069 1.0000 0.0144
-12.000 -1.3146 0.01895 0.01353 -0.0065 1.0000 0.0148
-11.750 -1.2908 0.01836 0.01289 -0.0061 1.0000 0.0152
-11.500 -1.2667 0.01780 0.01228 -0.0057 1.0000 0.0156
-11.250 -1.2421 0.01727 0.01169 -0.0053 1.0000 0.0159
-11.000 -1.2172 0.01677 0.01113 -0.0050 1.0000 0.0163
-10.750 -1.1920 0.01630 0.01060 -0.0047 1.0000 0.0166
-10.500 -1.1671 0.01574 0.01000 -0.0044 1.0000 0.0171
-10.250 -1.1416 0.01524 0.00948 -0.0041 1.0000 0.0178
-10.000 -1.1158 0.01480 0.00900 -0.0038 1.0000 0.0184
-9.750 -1.0897 0.01438 0.00856 -0.0036 1.0000 0.0190
-9.500 -1.0633 0.01400 0.00814 -0.0034 1.0000 0.0196
-9.250 -1.0367 0.01365 0.00774 -0.0032 1.0000 0.0202
-9.000 -1.0103 0.01322 0.00730 -0.0030 1.0000 0.0212
-8.750 -0.9835 0.01285 0.00692 -0.0028 1.0000 0.0222
-8.500 -0.9565 0.01252 0.00657 -0.0026 1.0000 0.0233
-8.250 -0.9292 0.01222 0.00625 -0.0025 1.0000 0.0242
-8.000 -0.9021 0.01186 0.00589 -0.0023 1.0000 0.0256
-7.750 -0.8748 0.01155 0.00557 -0.0022 1.0000 0.0271
-7.500 -0.8472 0.01127 0.00528 -0.0021 1.0000 0.0284
-7.250 -0.8196 0.01099 0.00499 -0.0020 1.0000 0.0300
-7.000 -0.7920 0.01070 0.00471 -0.0019 1.0000 0.0320
-6.750 -0.7641 0.01045 0.00445 -0.0018 1.0000 0.0338
-6.500 -0.7363 0.01018 0.00420 -0.0017 1.0000 0.0364
-6.250 -0.7083 0.00993 0.00396 -0.0016 1.0000 0.0394
-6.000 -0.6803 0.00969 0.00373 -0.0016 1.0000 0.0426
-5.750 -0.6522 0.00944 0.00351 -0.0015 1.0000 0.0466
-5.500 -0.6241 0.00921 0.00331 -0.0014 1.0000 0.0506
-5.250 -0.5959 0.00899 0.00311 -0.0014 1.0000 0.0558
-5.000 -0.5676 0.00875 0.00292 -0.0013 1.0000 0.0618
-4.750 -0.5393 0.00856 0.00275 -0.0013 1.0000 0.0677
-4.500 -0.5110 0.00833 0.00258 -0.0012 1.0000 0.0758
-4.250 -0.4826 0.00811 0.00242 -0.0012 1.0000 0.0855
-4.000 -0.4488 0.00792 0.00228 -0.0024 0.9630 0.0980
-3.750 -0.4229 0.00786 0.00217 -0.0015 0.9009 0.1110
-3.500 -0.3986 0.00789 0.00203 -0.0004 0.8296 0.1242
-3.250 -0.3720 0.00794 0.00189 0.0001 0.7543 0.1398
-3.000 -0.3444 0.00799 0.00177 0.0002 0.6820 0.1553
-2.750 -0.3162 0.00798 0.00166 0.0003 0.6298 0.1728
-2.500 -0.2878 0.00795 0.00156 0.0003 0.5840 0.1925
-2.250 -0.2593 0.00792 0.00147 0.0002 0.5425 0.2139
-2.000 -0.2307 0.00787 0.00140 0.0002 0.5134 0.2337
-1.750 -0.2019 0.00781 0.00134 0.0002 0.4925 0.2531
-1.500 -0.1733 0.00774 0.00129 0.0001 0.4709 0.2765
-1.250 -0.1445 0.00769 0.00125 0.0001 0.4515 0.2968
-1.000 -0.1156 0.00766 0.00122 0.0001 0.4369 0.3133
-0.750 -0.0867 0.00761 0.00120 0.0001 0.4238 0.3326
-0.500 -0.0579 0.00757 0.00119 0.0000 0.4107 0.3535
-0.250 -0.0290 0.00756 0.00118 0.0000 0.3971 0.3694
0.000 0.0000 0.00756 0.00118 0.0000 0.3828 0.3827
0.250 0.0290 0.00756 0.00118 0.0000 0.3694 0.3969
0.500 0.0579 0.00757 0.00119 0.0000 0.3534 0.4107
0.750 0.0867 0.00761 0.00120 -0.0001 0.3325 0.4239
1.000 0.1156 0.00766 0.00122 -0.0001 0.3134 0.4369
1.250 0.1445 0.00769 0.00125 -0.0001 0.2970 0.4514
1.500 0.1732 0.00773 0.00129 -0.0001 0.2765 0.4709
1.750 0.2019 0.00781 0.00134 -0.0002 0.2530 0.4925
2.000 0.2307 0.00787 0.00140 -0.0002 0.2336 0.5134
2.250 0.2593 0.00792 0.00147 -0.0002 0.2134 0.5428
2.500 0.2878 0.00795 0.00156 -0.0003 0.1930 0.5846
2.750 0.3162 0.00798 0.00166 -0.0003 0.1730 0.6298
3.000 0.3444 0.00799 0.00177 -0.0003 0.1550 0.6818
3.250 0.3721 0.00794 0.00189 -0.0001 0.1398 0.7534
3.500 0.3986 0.00789 0.00203 0.0004 0.1243 0.8295
3.750 0.4229 0.00786 0.00217 0.0016 0.1110 0.9015
4.000 0.4488 0.00792 0.00228 0.0024 0.0980 0.9630
4.250 0.4826 0.00812 0.00242 0.0012 0.0853 1.0000
4.500 0.5110 0.00834 0.00258 0.0012 0.0757 1.0000
4.750 0.5393 0.00856 0.00275 0.0013 0.0677 1.0000
5.000 0.5676 0.00875 0.00292 0.0013 0.0618 1.0000
5.250 0.5959 0.00899 0.00311 0.0014 0.0557 1.0000
5.500 0.6241 0.00921 0.00331 0.0014 0.0506 1.0000
5.750 0.6523 0.00944 0.00351 0.0015 0.0467 1.0000
6.000 0.6803 0.00968 0.00373 0.0016 0.0427 1.0000
6.250 0.7084 0.00993 0.00396 0.0016 0.0393 1.0000
6.500 0.7363 0.01018 0.00420 0.0017 0.0364 1.0000
6.750 0.7642 0.01045 0.00445 0.0018 0.0338 1.0000
7.000 0.7920 0.01070 0.00471 0.0019 0.0320 1.0000
7.250 0.8197 0.01099 0.00499 0.0020 0.0300 1.0000
7.500 0.8473 0.01127 0.00528 0.0021 0.0284 1.0000
7.750 0.8748 0.01155 0.00557 0.0022 0.0271 1.0000
8.000 0.9022 0.01186 0.00589 0.0023 0.0256 1.0000
8.250 0.9293 0.01222 0.00625 0.0025 0.0242 1.0000
8.500 0.9566 0.01252 0.00657 0.0026 0.0233 1.0000
8.750 0.9836 0.01285 0.00692 0.0028 0.0222 1.0000
9.000 1.0104 0.01322 0.00730 0.0030 0.0212 1.0000
9.250 1.0368 0.01364 0.00774 0.0032 0.0202 1.0000
9.500 1.0634 0.01400 0.00814 0.0034 0.0196 1.0000
9.750 1.0898 0.01438 0.00856 0.0036 0.0190 1.0000
10.000 1.1159 0.01480 0.00900 0.0038 0.0184 1.0000
10.250 1.1418 0.01524 0.00948 0.0040 0.0178 1.0000
10.500 1.1672 0.01573 0.01000 0.0043 0.0172 1.0000
10.750 1.1921 0.01630 0.01061 0.0046 0.0166 1.0000
11.000 1.2174 0.01677 0.01113 0.0050 0.0163 1.0000
11.250 1.2423 0.01727 0.01169 0.0053 0.0159 1.0000
11.500 1.2669 0.01780 0.01228 0.0056 0.0156 1.0000
11.750 1.2910 0.01837 0.01289 0.0060 0.0152 1.0000
12.000 1.3148 0.01895 0.01353 0.0064 0.0148 1.0000
12.250 1.3381 0.01958 0.01420 0.0069 0.0144 1.0000
12.500 1.3608 0.02027 0.01494 0.0073 0.0141 1.0000
12.750 1.3822 0.02109 0.01582 0.0079 0.0137 1.0000
13.000 1.4031 0.02193 0.01674 0.0085 0.0135 1.0000
13.250 1.4243 0.02269 0.01757 0.0091 0.0133 1.0000
13.500 1.4446 0.02350 0.01847 0.0097 0.0132 1.0000
13.750 1.4639 0.02437 0.01943 0.0104 0.0130 1.0000
14.000 1.4822 0.02530 0.02045 0.0111 0.0128 1.0000
14.250 1.4992 0.02630 0.02154 0.0119 0.0126 1.0000
14.500 1.5147 0.02739 0.02272 0.0128 0.0125 1.0000
14.750 1.5283 0.02858 0.02399 0.0138 0.0123 1.0000
15.000 1.5393 0.02989 0.02541 0.0149 0.0122 1.0000
15.250 1.5438 0.03137 0.02699 0.0165 0.0120 1.0000
15.500 1.5436 0.03335 0.02908 0.0177 0.0119 1.0000
15.750 1.5407 0.03626 0.03212 0.0170 0.0118 1.0000
16.000 1.5342 0.04082 0.03683 0.0137 0.0117 1.0000
16.250 1.5220 0.04752 0.04371 0.0078 0.0117 1.0000
16.500 1.4997 0.05587 0.05226 0.0016 0.0117 1.0000
16.750 1.4634 0.06585 0.06243 -0.0047 0.0117 1.0000
17.000 1.4176 0.07712 0.07389 -0.0111 0.0118 1.0000
17.250 1.3670 0.08928 0.08623 -0.0178 0.0119 1.0000
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Polar data table (+)
Polar graphs
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