RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 500,000 Max Cl/Cd: 82.26 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1410-il-500000.txt Download as CSV file: xf-rg1410-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 10% AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7199 0.05362 0.05091 -0.0556 1.0000 0.0153
-11.000 -0.7365 0.04933 0.04647 -0.0580 1.0000 0.0152
-10.750 -0.7594 0.04581 0.04279 -0.0570 1.0000 0.0152
-10.500 -0.7850 0.04291 0.03971 -0.0529 1.0000 0.0152
-10.250 -0.8025 0.03945 0.03601 -0.0495 1.0000 0.0153
-10.000 -0.8164 0.03573 0.03199 -0.0460 1.0000 0.0154
-9.750 -0.8201 0.03279 0.02881 -0.0428 1.0000 0.0157
-9.500 -0.8136 0.03108 0.02697 -0.0405 1.0000 0.0160
-9.250 -0.8064 0.02925 0.02495 -0.0380 1.0000 0.0163
-9.000 -0.7959 0.02779 0.02333 -0.0358 1.0000 0.0167
-8.750 -0.7846 0.02632 0.02168 -0.0335 1.0000 0.0171
-8.500 -0.7723 0.02491 0.02008 -0.0313 1.0000 0.0177
-8.250 -0.7601 0.02326 0.01819 -0.0289 1.0000 0.0182
-8.000 -0.7450 0.02216 0.01688 -0.0269 1.0000 0.0189
-7.750 -0.7274 0.02179 0.01634 -0.0251 1.0000 0.0196
-7.500 -0.7156 0.01917 0.01349 -0.0229 1.0000 0.0206
-7.250 -0.6982 0.01837 0.01264 -0.0213 1.0000 0.0214
-7.000 -0.6772 0.01764 0.01183 -0.0203 0.9997 0.0222
-6.750 -0.6432 0.01674 0.01082 -0.0219 0.9974 0.0233
-6.500 -0.6081 0.01603 0.01000 -0.0236 0.9951 0.0245
-6.250 -0.5747 0.01510 0.00894 -0.0250 0.9928 0.0259
-6.000 -0.5430 0.01405 0.00785 -0.0262 0.9896 0.0275
-5.750 -0.5082 0.01347 0.00723 -0.0278 0.9867 0.0290
-5.500 -0.4719 0.01299 0.00671 -0.0297 0.9845 0.0310
-5.250 -0.4379 0.01254 0.00619 -0.0311 0.9815 0.0327
-5.000 -0.4069 0.01174 0.00538 -0.0320 0.9770 0.0358
-4.750 -0.3713 0.01134 0.00496 -0.0336 0.9740 0.0393
-4.500 -0.3344 0.01082 0.00445 -0.0356 0.9717 0.0471
-4.250 -0.3025 0.01035 0.00404 -0.0365 0.9670 0.0631
-4.000 -0.2688 0.00989 0.00370 -0.0378 0.9625 0.0897
-3.750 -0.2319 0.00946 0.00340 -0.0399 0.9596 0.1206
-3.500 -0.1939 0.00902 0.00314 -0.0421 0.9574 0.1626
-3.250 -0.1652 0.00861 0.00291 -0.0424 0.9503 0.2090
-3.000 -0.1317 0.00814 0.00268 -0.0437 0.9454 0.2707
-2.750 -0.1018 0.00761 0.00248 -0.0443 0.9387 0.3595
-2.500 -0.0728 0.00705 0.00228 -0.0447 0.9307 0.4608
-2.250 -0.0456 0.00659 0.00213 -0.0445 0.9210 0.5502
-2.000 -0.0186 0.00613 0.00200 -0.0442 0.9111 0.6487
-1.750 0.0066 0.00585 0.00200 -0.0432 0.8993 0.7344
-1.500 0.0322 0.00578 0.00201 -0.0422 0.8863 0.7860
-1.250 0.0583 0.00576 0.00201 -0.0414 0.8729 0.8170
-1.000 0.0844 0.00577 0.00200 -0.0406 0.8589 0.8396
-0.750 0.1101 0.00580 0.00200 -0.0397 0.8442 0.8571
-0.500 0.1356 0.00583 0.00199 -0.0388 0.8288 0.8719
-0.250 0.1607 0.00588 0.00198 -0.0378 0.8122 0.8852
0.000 0.1853 0.00595 0.00197 -0.0367 0.7939 0.8977
0.250 0.2093 0.00600 0.00199 -0.0354 0.7737 0.9091
0.500 0.2335 0.00607 0.00199 -0.0342 0.7540 0.9195
0.750 0.2578 0.00615 0.00200 -0.0331 0.7354 0.9295
1.000 0.2826 0.00624 0.00203 -0.0321 0.7165 0.9390
1.250 0.3087 0.00634 0.00205 -0.0314 0.6941 0.9478
1.500 0.3344 0.00646 0.00208 -0.0306 0.6715 0.9571
1.750 0.3671 0.00659 0.00213 -0.0315 0.6496 0.9624
2.000 0.3973 0.00673 0.00219 -0.0318 0.6267 0.9694
2.250 0.4340 0.00690 0.00226 -0.0337 0.6016 0.9736
2.500 0.4722 0.00707 0.00233 -0.0359 0.5754 0.9771
2.750 0.5061 0.00726 0.00242 -0.0372 0.5464 0.9818
3.000 0.5419 0.00747 0.00249 -0.0390 0.5131 0.9852
3.250 0.5781 0.00767 0.00258 -0.0409 0.4814 0.9884
3.750 0.6464 0.00811 0.00279 -0.0440 0.4194 0.9955
4.000 0.6808 0.00835 0.00291 -0.0457 0.3849 0.9986
4.250 0.7066 0.00859 0.00304 -0.0455 0.3534 1.0000
4.500 0.7232 0.00883 0.00318 -0.0435 0.3247 1.0000
4.750 0.7388 0.00912 0.00334 -0.0413 0.2927 1.0000
5.000 0.7541 0.00946 0.00354 -0.0390 0.2597 1.0000
5.250 0.7704 0.00984 0.00377 -0.0369 0.2251 1.0000
5.500 0.7881 0.01025 0.00403 -0.0351 0.1925 1.0000
5.750 0.8072 0.01067 0.00432 -0.0335 0.1686 1.0000
6.000 0.8281 0.01105 0.00462 -0.0323 0.1517 1.0000
6.250 0.8499 0.01141 0.00495 -0.0313 0.1373 1.0000
6.500 0.8722 0.01178 0.00527 -0.0303 0.1227 1.0000
6.750 0.8948 0.01215 0.00560 -0.0295 0.1087 1.0000
7.000 0.9172 0.01255 0.00595 -0.0286 0.0960 1.0000
7.250 0.9394 0.01298 0.00636 -0.0277 0.0852 1.0000
7.500 0.9605 0.01352 0.00684 -0.0266 0.0757 1.0000
7.750 0.9836 0.01388 0.00723 -0.0259 0.0691 1.0000
8.000 1.0049 0.01439 0.00773 -0.0249 0.0618 1.0000
8.250 1.0270 0.01483 0.00817 -0.0240 0.0553 1.0000
8.500 1.0482 0.01534 0.00872 -0.0230 0.0499 1.0000
8.750 1.0696 0.01582 0.00920 -0.0221 0.0450 1.0000
9.000 1.0894 0.01644 0.00985 -0.0209 0.0406 1.0000
9.250 1.1110 0.01688 0.01031 -0.0200 0.0368 1.0000
9.500 1.1278 0.01771 0.01117 -0.0184 0.0330 1.0000
9.750 1.1490 0.01815 0.01168 -0.0175 0.0303 1.0000
10.000 1.1666 0.01885 0.01238 -0.0161 0.0273 1.0000
10.250 1.1829 0.01962 0.01323 -0.0144 0.0245 1.0000
10.500 1.2010 0.02022 0.01387 -0.0131 0.0221 1.0000
10.750 1.2088 0.02146 0.01514 -0.0104 0.0200 1.0000
11.000 1.2239 0.02206 0.01587 -0.0085 0.0187 1.0000
11.250 1.2355 0.02286 0.01673 -0.0062 0.0174 1.0000
11.500 1.2444 0.02381 0.01774 -0.0038 0.0164 1.0000
11.750 1.2415 0.02558 0.01959 -0.0001 0.0154 1.0000
12.000 1.2502 0.02664 0.02076 0.0021 0.0150 1.0000
12.250 1.2583 0.02776 0.02201 0.0041 0.0143 1.0000
12.500 1.2645 0.02905 0.02340 0.0060 0.0137 1.0000
12.750 1.2706 0.03037 0.02481 0.0077 0.0131 1.0000
13.000 1.2751 0.03189 0.02643 0.0092 0.0127 1.0000
13.250 1.2754 0.03386 0.02850 0.0107 0.0124 1.0000
13.500 1.2694 0.03656 0.03129 0.0120 0.0119 1.0000
13.750 1.2603 0.03986 0.03475 0.0130 0.0116 1.0000
14.000 1.2625 0.04214 0.03717 0.0132 0.0114 1.0000
14.250 1.2598 0.04512 0.04031 0.0132 0.0111 1.0000
14.500 1.2553 0.04848 0.04381 0.0128 0.0111 1.0000
14.750 1.2507 0.05206 0.04754 0.0119 0.0109 1.0000
15.000 1.2439 0.05614 0.05178 0.0106 0.0106 1.0000
15.250 1.2357 0.06062 0.05640 0.0089 0.0105 1.0000
15.500 1.2255 0.06561 0.06155 0.0067 0.0105 1.0000
15.750 1.2160 0.07079 0.06687 0.0041 0.0103 1.0000
16.000 1.2013 0.07701 0.07326 0.0010 0.0103 1.0000
16.250 1.1882 0.08331 0.07971 -0.0024 0.0102 1.0000
16.500 1.1735 0.09015 0.08670 -0.0063 0.0101 1.0000
16.750 1.1589 0.09727 0.09396 -0.0104 0.0101 1.0000
17.000 1.1388 0.10571 0.10257 -0.0152 0.0102 1.0000
17.250 1.1208 0.11412 0.11113 -0.0202 0.0102 1.0000
17.500 1.0990 0.12367 0.12083 -0.0259 0.0102 1.0000
17.750 1.0738 0.13447 0.13180 -0.0324 0.0104 1.0000
18.000 1.0410 0.14783 0.14534 -0.0404 0.0106 1.0000
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