BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 500,000 Max Cl/Cd: 59.35 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b540ols-il-500000.txt Download as CSV file: xf-b540ols-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.1549 0.08697 0.08392 0.0136 1.0000 0.0218
-14.750 -1.1967 0.07503 0.07174 0.0054 1.0000 0.0216
-14.500 -1.2233 0.06618 0.06268 -0.0009 1.0000 0.0216
-14.250 -1.2414 0.05888 0.05519 -0.0064 1.0000 0.0216
-14.000 -1.2538 0.05272 0.04885 -0.0113 1.0000 0.0217
-13.750 -1.2628 0.04761 0.04355 -0.0153 1.0000 0.0218
-13.500 -1.2699 0.04355 0.03931 -0.0176 1.0000 0.0220
-13.250 -1.2754 0.04048 0.03606 -0.0180 1.0000 0.0222
-13.000 -1.2783 0.03818 0.03361 -0.0167 1.0000 0.0224
-12.750 -1.2748 0.03617 0.03142 -0.0155 1.0000 0.0227
-12.500 -1.2666 0.03427 0.02935 -0.0144 1.0000 0.0230
-12.250 -1.2553 0.03253 0.02743 -0.0135 1.0000 0.0234
-12.000 -1.2413 0.03099 0.02570 -0.0125 1.0000 0.0238
-11.750 -1.2248 0.02969 0.02422 -0.0117 1.0000 0.0241
-11.500 -1.2117 0.02750 0.02187 -0.0107 1.0000 0.0247
-11.250 -1.1940 0.02610 0.02041 -0.0100 1.0000 0.0253
-11.000 -1.1733 0.02517 0.01944 -0.0094 1.0000 0.0259
-10.750 -1.1518 0.02428 0.01848 -0.0089 1.0000 0.0267
-10.500 -1.1300 0.02335 0.01744 -0.0083 1.0000 0.0275
-10.250 -1.1076 0.02244 0.01641 -0.0078 1.0000 0.0282
-10.000 -1.0840 0.02170 0.01553 -0.0073 1.0000 0.0288
-9.750 -1.0642 0.02015 0.01394 -0.0066 1.0000 0.0299
-9.500 -1.0405 0.01938 0.01315 -0.0061 1.0000 0.0309
-9.250 -1.0160 0.01872 0.01243 -0.0058 1.0000 0.0320
-9.000 -0.9909 0.01812 0.01175 -0.0054 1.0000 0.0333
-8.750 -0.9660 0.01742 0.01096 -0.0050 1.0000 0.0346
-8.500 -0.9420 0.01653 0.01008 -0.0046 1.0000 0.0363
-8.250 -0.9162 0.01600 0.00952 -0.0044 1.0000 0.0381
-8.000 -0.8898 0.01553 0.00898 -0.0041 1.0000 0.0398
-7.750 -0.8647 0.01474 0.00816 -0.0038 1.0000 0.0421
-7.500 -0.8383 0.01426 0.00768 -0.0036 1.0000 0.0446
-7.250 -0.8112 0.01391 0.00727 -0.0034 1.0000 0.0472
-7.000 -0.7852 0.01323 0.00661 -0.0031 1.0000 0.0508
-6.750 -0.7580 0.01285 0.00620 -0.0030 1.0000 0.0544
-6.500 -0.7311 0.01234 0.00569 -0.0028 1.0000 0.0590
-6.250 -0.7037 0.01198 0.00534 -0.0027 1.0000 0.0642
-6.000 -0.6765 0.01151 0.00490 -0.0025 1.0000 0.0709
-5.750 -0.6489 0.01115 0.00455 -0.0024 1.0000 0.0786
-5.500 -0.6212 0.01080 0.00423 -0.0023 1.0000 0.0881
-5.250 -0.5937 0.01041 0.00391 -0.0022 1.0000 0.1010
-5.000 -0.5660 0.01002 0.00361 -0.0021 1.0000 0.1175
-4.750 -0.5383 0.00966 0.00335 -0.0020 1.0000 0.1369
-4.500 -0.5105 0.00934 0.00312 -0.0020 1.0000 0.1584
-4.250 -0.4827 0.00902 0.00292 -0.0019 1.0000 0.1823
-4.000 -0.4547 0.00873 0.00274 -0.0019 1.0000 0.2070
-3.750 -0.4267 0.00847 0.00258 -0.0018 1.0000 0.2326
-3.500 -0.3988 0.00821 0.00245 -0.0017 1.0000 0.2585
-3.250 -0.3707 0.00800 0.00233 -0.0016 1.0000 0.2834
-3.000 -0.3427 0.00780 0.00223 -0.0015 1.0000 0.3083
-2.750 -0.3147 0.00762 0.00216 -0.0014 1.0000 0.3318
-2.500 -0.2866 0.00747 0.00210 -0.0013 1.0000 0.3546
-2.250 -0.2586 0.00735 0.00205 -0.0012 1.0000 0.3754
-2.000 -0.2307 0.00722 0.00201 -0.0010 1.0000 0.3945
-1.750 -0.2030 0.00710 0.00197 -0.0008 1.0000 0.4125
-1.500 -0.1704 0.00699 0.00194 -0.0016 0.9910 0.4307
-1.250 -0.1289 0.00690 0.00193 -0.0043 0.9431 0.4521
-1.000 -0.1039 0.00698 0.00189 -0.0029 0.8597 0.4704
-0.750 -0.0809 0.00719 0.00183 -0.0012 0.7644 0.4890
-0.500 -0.0549 0.00739 0.00178 -0.0005 0.6804 0.5107
-0.250 -0.0276 0.00750 0.00175 -0.0002 0.6179 0.5381
0.000 0.0000 0.00753 0.00174 0.0000 0.5724 0.5725
0.250 0.0277 0.00750 0.00175 0.0002 0.5380 0.6177
0.500 0.0550 0.00739 0.00178 0.0005 0.5107 0.6803
0.750 0.0810 0.00719 0.00183 0.0012 0.4890 0.7643
1.000 0.1040 0.00698 0.00189 0.0028 0.4704 0.8598
1.250 0.1290 0.00690 0.00193 0.0042 0.4520 0.9430
1.500 0.1705 0.00699 0.00194 0.0016 0.4306 0.9910
1.750 0.2031 0.00710 0.00197 0.0008 0.4126 1.0000
2.000 0.2308 0.00722 0.00201 0.0010 0.3946 1.0000
2.250 0.2587 0.00735 0.00205 0.0011 0.3754 1.0000
2.500 0.2867 0.00747 0.00210 0.0013 0.3546 1.0000
2.750 0.3147 0.00762 0.00216 0.0014 0.3319 1.0000
3.000 0.3428 0.00780 0.00223 0.0015 0.3083 1.0000
3.250 0.3708 0.00800 0.00233 0.0016 0.2834 1.0000
3.500 0.3989 0.00821 0.00245 0.0017 0.2586 1.0000
3.750 0.4268 0.00847 0.00258 0.0018 0.2327 1.0000
4.000 0.4548 0.00873 0.00274 0.0018 0.2070 1.0000
4.250 0.4827 0.00902 0.00292 0.0019 0.1823 1.0000
4.500 0.5106 0.00934 0.00312 0.0020 0.1583 1.0000
4.750 0.5384 0.00966 0.00335 0.0020 0.1369 1.0000
5.000 0.5661 0.01002 0.00361 0.0021 0.1175 1.0000
5.250 0.5937 0.01041 0.00390 0.0022 0.1010 1.0000
5.500 0.6213 0.01080 0.00423 0.0023 0.0881 1.0000
5.750 0.6490 0.01115 0.00455 0.0024 0.0786 1.0000
6.000 0.6766 0.01151 0.00490 0.0025 0.0708 1.0000
6.250 0.7037 0.01198 0.00534 0.0026 0.0642 1.0000
6.500 0.7312 0.01234 0.00569 0.0028 0.0590 1.0000
6.750 0.7581 0.01284 0.00620 0.0030 0.0544 1.0000
7.000 0.7852 0.01323 0.00661 0.0031 0.0508 1.0000
7.250 0.8112 0.01391 0.00727 0.0034 0.0472 1.0000
7.500 0.8384 0.01426 0.00768 0.0035 0.0446 1.0000
7.750 0.8648 0.01474 0.00816 0.0037 0.0421 1.0000
8.000 0.8899 0.01553 0.00898 0.0041 0.0398 1.0000
8.250 0.9163 0.01600 0.00952 0.0044 0.0381 1.0000
8.500 0.9421 0.01654 0.01008 0.0046 0.0363 1.0000
8.750 0.9661 0.01742 0.01096 0.0050 0.0346 1.0000
9.000 0.9910 0.01812 0.01176 0.0054 0.0333 1.0000
9.250 1.0161 0.01871 0.01243 0.0057 0.0320 1.0000
9.500 1.0406 0.01938 0.01315 0.0061 0.0309 1.0000
9.750 1.0643 0.02015 0.01394 0.0065 0.0299 1.0000
10.000 1.0841 0.02170 0.01554 0.0072 0.0288 1.0000
10.250 1.1077 0.02244 0.01641 0.0077 0.0282 1.0000
10.500 1.1301 0.02335 0.01744 0.0083 0.0275 1.0000
10.750 1.1519 0.02429 0.01848 0.0088 0.0267 1.0000
11.000 1.1734 0.02517 0.01944 0.0094 0.0260 1.0000
11.250 1.1942 0.02610 0.02041 0.0099 0.0253 1.0000
11.500 1.2119 0.02750 0.02187 0.0107 0.0247 1.0000
11.750 1.2250 0.02969 0.02422 0.0117 0.0241 1.0000
12.000 1.2415 0.03099 0.02570 0.0125 0.0238 1.0000
12.250 1.2555 0.03254 0.02743 0.0134 0.0234 1.0000
12.500 1.2669 0.03427 0.02935 0.0144 0.0230 1.0000
12.750 1.2752 0.03617 0.03142 0.0154 0.0227 1.0000
13.000 1.2788 0.03818 0.03361 0.0167 0.0224 1.0000
13.250 1.2760 0.04048 0.03607 0.0179 0.0222 1.0000
13.500 1.2706 0.04355 0.03931 0.0175 0.0220 1.0000
13.750 1.2637 0.04759 0.04352 0.0151 0.0218 1.0000
14.000 1.2550 0.05269 0.04881 0.0112 0.0217 1.0000
14.250 1.2427 0.05883 0.05514 0.0063 0.0216 1.0000
14.500 1.2250 0.06608 0.06258 0.0008 0.0216 1.0000
14.750 1.1990 0.07487 0.07157 -0.0055 0.0216 1.0000
15.000 1.1561 0.08701 0.08396 -0.0138 0.0218 1.0000
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Polar data table (+)
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